81 FR 67098 - Airworthiness Directives; General Electric Company Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 190 (September 30, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 190 (September 30, 2016)
| Page Range | 67098-67100 | |
| FR Document | 2016-23740 |
[Federal Register Volume 81, Number 190 (Friday, September 30, 2016)] [Rules and Regulations] [Pages 67098-67100] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-23740] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5307; Directorate Identifier 2016-NE-08-AD; Amendment 39-18658; AD 2016-19-09] RIN 2120-AA64 Airworthiness Directives; General Electric Company Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with high-pressure compressor (HPC) stage 8-10 spool, part numbers (P/Ns) 1694M80G04, 1844M90G01, or [[Page 67099]] 1844M90G02, installed. This AD was prompted by reports of cracks found on the seal teeth of the HPC stage 8-10 spool. This AD requires eddy current inspections (ECIs) or fluorescent penetrant inspections (FPIs) of the HPC stage 8-10 spool seal teeth and removing from service those parts that fail inspection. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane. DATES: This AD is effective November 4, 2016. ADDRESSES: For service information identified in this final rule, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513-552-3272; email: [email protected]. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-5307. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 5307; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Document Management Facility, 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: John Frost, Aerospace Engineer, Engine Certification Office, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all GE GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with HPC stage 8-10 spool, P/Ns 1694M80G04, 1844M90G01, or 1844M90G02, installed. The NPRM published in the Federal Register on April 11, 2016 (81 FR 21286). The NPRM was prompted by reports of cracks found on the seal teeth of the HPC stage 8-10 spool during shop visits. The cracks initiated due to higher than intended temperatures at the seal teeth and damage to seal teeth coating from heavy rubs into the honeycomb. GE is developing a modification to address the unsafe condition. The NPRM proposed to require ECIs or FPIs of the HPC stage 8-10 spool seal teeth and removing from service those parts that fail inspection. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Support of the NPRM as Written Boeing and United Airlines support the NPRM as written. Request To Clarify Performance of ECI and FPI Nao Seto requested that the FAA clarify with which service information the ECI and FPI will be performed. We agree. We added a statement to compliance paragraph (e) in this AD indicating the GE service documents in which guidance can be found for performing the ECI and the FPI. Request To Clarify Supplementary Information General Electric Aviation requested that the Discussion paragraph be changed to read as follows: ``Based on recent testing, change the root cause of crack initiation from that of degraded surface properties caused by an alloy depletion zone (ADZ) to cracks initiated due to higher than intended temperatures at the seal teeth and damage to seal teeth coating from heavy rubs into the honeycomb.'' Recent testing and analysis have shown that the temperatures in the seal teeth are higher than design intent. This elevated temperature increases the stress in the region of the seal teeth, aligning with the cracking observed. GE also completed testing to determine the impact of alloy depletion zone on material capability. Testing showed material capability was not impacted. We agree. We oversaw the recent testing and analysis which supports the requested change. We changed the Discussion paragraph of this AD accordingly. Request To Add Ultrasonic Inspection (USI) to the Compliance GE requested that USI be added to the Compliance section as an alternate inspection method. Additionally, GE requested that we revise the Related Information paragraph (h)(2) of this AD by updating the service information to revision 1 based on the qualifying USI procedure. We disagree. USI procedures are not an acceptable alternative to the existing ECI and FPI procedures specified in this AD. A USI is not a viable procedure for compliance at this time, therefore, we are not updating the service information in paragraph (h)(2) to Revision 1. We may consider an AMOC after sufficient substantiated data is presented to the FAA. We did not change this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed. Related Service Information We reviewed GE Service Bulletins SB 72-1141 R00, dated December 2, 2015; and SB 72-1142 R00, dated November 30, 2015. The service information describes procedures for inspecting the HPC stage 8-10 spool seal teeth. Costs of Compliance We estimate that this AD affects 54 engines installed on airplanes of U.S. registry. We also estimate that it will take about 1 hour per engine to comply with this AD. The average labor rate is $85 per hour. We estimate 14 parts will fail inspection at a pro-rated cost of $400,000 per part. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $5,604,590. 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. We are 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 [[Page 67100]] 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) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and (4) 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. Adoption of 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 (AD): 2016-19-09 General Electric Company: Amendment 39-18658; Docket No. FAA-2016-5307; Directorate Identifier 2016-NE-08-AD. (a) Effective Date This AD is effective November 4, 2016. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) GE90-76B, GE90- 77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with a high- pressure compressor (HPC) stage 8-10 spool, part numbers 1694M80G04, 1844M90G01, or 1844M90G02, installed. (d) Unsafe Condition This AD was prompted by reports of cracks found on the seal teeth of the HPC stage 8-10 spool. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Perform an eddy current inspection (ECI) or fluorescent penetrant inspection (FPI) of the seal teeth of the HPC stage 8-10 spool as follows: (i) For HPC stage 8-10 spools with fewer than 11,000 cycles since new (CSN) on the effective day of this AD, inspect at the next shop visit after reaching 6,000 CSN, not to exceed 12,500 CSN. (ii) For HPC stage 8-10 spools with 11,000 CSN or more on the effective day of this AD, inspect within the next 1,500 cycles in service. (iii) Thereafter, inspect the seal teeth of the HPC stage 8-10 spool at each shop visit. (2) Remove from service any HPC stage 8-10 spool that fails the ECI or FPI required by paragraph (e)(1) of this AD and replace with a part eligible for installation. (3) Guidance on performing the ECI and the FPI can be found in GE Service Bulletins (SBs) SB 72-1141 R00, dated December 2, 2015 and SB 72-1142 R00, dated November 30, 2015. (f) Definition For the purpose of this AD, an engine shop visit is the induction of an engine into the shop for maintenance during which the compressor discharge pressure seal face is exposed. (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: [email protected]. (h) Related Information (1) For more information about this AD, contact John Frost, Aerospace Engineer, Engine Certification Office, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238- 7199; email: [email protected]. (2) GE SB 72-1141, R00, dated December 2, 2015 and GE SB 72- 1142, R00, dated November 30, 2015, which are not incorporated by reference in this AD, can be obtained from GE, using the contact information in paragraph (h)(3) of this AD. (3) For service information identified in this AD, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513-552-3272; email: [email protected]. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (i) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on September 26, 2016. Colleen M. D'Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-23740 Filed 9-29-16; 8:45 am] BILLING CODE 4910-13-P
![67098 Federal Register / Vol. 81, No. 190 / Friday, September 30, 2016 / Rules and Regulations
or unusual design feature, special must take into account that some pilot- List of Subjects in 14 CFR Part 25
conditions are prescribed under the demanded maneuvers (e.g., rapid roll) Aircraft, Aviation safety, Reporting
provisions of § 21.16. are necessarily associated with intended and recordkeeping requirements.
Special conditions are initially full performance, which may saturate
applicable to the model for which they ■ The authority citation for these
the surface. Therefore, simple alerting
are issued. Should the type certificate special conditions is as follows:
systems function in both intended and
for that model be amended later to unexpected control-limiting situations. Authority: 49 U.S.C. 106(g), 40113, 44701,
include any other model that As a result, they must be properly 44702, 44704.
incorporates the same novel or unusual balanced between providing necessary The Special Conditions
design features, or should any other crew awareness and being a potential
model already included on the same Accordingly, pursuant to the
nuisance to the flightcrew. A monitoring
type certificate be modified to authority delegated to me by the
system that compares airplane motion
incorporate the same novel or unusual Administrator, the following special
and surface deflection with pilot inputs
design feature, these special conditions conditions are issued as part of the type
could help reduce nuisance alerting.
would also apply to the other model certification basis for the Embraer S.A.
under § 21.101. These special conditions also address Model ERJ 190–300 series airplanes.
In addition to the applicable flight control system mode 1. In addition to the requirements of
airworthiness regulations and special annunciation. Suitable mode 14 CFR 25.143, 25.671, and 25.672, the
conditions, the ERJ 190–300 must annunciation must be provided to the following requirements apply:
comply with the fuel vent and exhaust flightcrew for events that significantly a. The system design must ensure that
emission requirements of 14 CFR part change the operating mode of the the flightcrew is made suitably aware
34 and the noise-certification system but do not merit the classic whenever the primary control means
requirements of 14 CFR part 36. ‘‘failure warning.’’ nears the limit of control authority.
The FAA issues special conditions, as These special conditions contain the Note: The term ‘‘suitably aware’’ indicates
defined in 14 CFR 11.19, in accordance additional safety standards that the annunciations provided to the flightcrew are
with § 11.38, and they become part of Administrator considers necessary to appropriately balanced between nuisance
the type certification basis under establish a level of safety equivalent to and that necessary for crew awareness.
§ 21.101. that established by the existing b. If the design of the flight control
Novel or Unusual Design Features airworthiness standards. system has multiple modes of operation,
The ERJ 190–300 will incorporate the a means must be provided to indicate to
Applicability
following novel or unusual design the flightcrew any mode that
features: A fly-by-wire EFCS and no As discussed above, these special significantly changes or degrades the
direct coupling from the flight deck conditions are applicable to the ERJ normal handling or operational
controller to the control surface. 190–300 series airplanes. Should characteristics of the airplane.
Embraer S.A. apply at a later date for a Issued in Renton, Washington, on
Discussion change to the type certificate to include September 23, 2016.
As a result of the EFCS and lack of another model incorporating the same Michael Kaszycki,
direct coupling from the flight deck novel or unusual design feature, these Assistant Manager, Transport Airplane
controller to the control surface, the special conditions would apply to that Directorate, Aircraft Certification Service.
pilot is not aware of the actual control model as well. [FR Doc. 2016–23665 Filed 9–29–16; 8:45 am]
surface position. Some unusual flight BILLING CODE 4910–13–P
conditions, arising from atmospheric Conclusion
conditions and/or airplane or engine This action affects only certain novel
failures, may result in full or nearly full or unusual design features on one model DEPARTMENT OF TRANSPORTATION
surface deflection. Unless the flightcrew of airplanes. It is not a rule of general
is made aware of excessive deflection or Federal Aviation Administration
applicability.
impending control surface limiting,
piloted or auto-flight system control of The substance of these special 14 CFR Part 39
the airplane might be inadvertently conditions has been subjected to the
notice and comment period in several [Docket No. FAA–2016–5307; Directorate
continued in such a manner to cause Identifier 2016–NE–08–AD; Amendment 39–
loss of control or other unsafe stability prior instances and has been derived 18658; AD 2016–19–09]
or performance characteristics. The without substantive change from those
previously issued. It is unlikely that RIN 2120–AA64
airworthiness standards do not contain
adequate or appropriate safety standards prior public comment would result in a
significant change from the substance Airworthiness Directives; General
for the conditions that result from the Electric Company Turbofan Engines
EFCS and lack of direct coupling from contained herein. Therefore, because a
the flight deck controller to the control delay would significantly affect the AGENCY: Federal Aviation
surface. certification of the airplane, the FAA Administration (FAA), DOT.
To establish a level of safety has determined that prior public notice ACTION: Final rule.
equivalent to that established in the and comment are unnecessary and
asabaliauskas on DSK3SPTVN1PROD with RULES
regulations, these special conditions are impracticable, and good cause exists for SUMMARY: We are adopting a new
established. These special conditions adopting these special conditions upon airworthiness directive (AD) for all
require that the flightcrew receive a publication in the Federal Register. The General Electric Company (GE) GE90–
suitable flight control position FAA is requesting comments to allow 76B, GE90–77B, GE90–85B, GE90–90B,
annunciation when a flight condition interested persons to submit views that and GE90–94B turbofan engines with
exists in which nearly full surface may not have been submitted in high-pressure compressor (HPC) stage
authority (not crew-commanded) is response to the prior opportunities for 8–10 spool, part numbers (P/Ns)
being used. Suitability of such a display comment described above. 1694M80G04, 1844M90G01, or
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![67100 Federal Register / Vol. 81, No. 190 / Friday, September 30, 2016 / Rules and Regulations
that is likely to exist or develop on (d) Unsafe Condition (i) Material Incorporated by Reference
products identified in this rulemaking This AD was prompted by reports of cracks None.
action. found on the seal teeth of the HPC stage 8– Issued in Burlington, Massachusetts, on
10 spool. We are issuing this AD to prevent September 26, 2016.
Regulatory Findings failure of the HPC stage 8–10 spool,
Colleen M. D’Alessandro,
This AD will not have federalism uncontained rotor release, damage to the
implications under Executive Order engine, and damage to the airplane. Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
13132. This AD will not have a (e) Compliance
substantial direct effect on the States, on [FR Doc. 2016–23740 Filed 9–29–16; 8:45 am]
Comply with this AD within the
the relationship between the national compliance times specified, unless already
BILLING CODE 4910–13–P
government and the States, or on the done.
distribution of power and (1) Perform an eddy current inspection
responsibilities among the various DEPARTMENT OF TRANSPORTATION
(ECI) or fluorescent penetrant inspection
levels of government. (FPI) of the seal teeth of the HPC stage 8–10 Federal Aviation Administration
For the reasons discussed above, I spool as follows:
certify that this AD: (i) For HPC stage 8–10 spools with fewer
14 CFR Part 39
(1) Is not a ‘‘significant regulatory than 11,000 cycles since new (CSN) on the
action’’ under Executive Order 12866, effective day of this AD, inspect at the next [Docket No. FAA–2015–4866; Directorate
(2) Is not a ‘‘significant rule’’ under shop visit after reaching 6,000 CSN, not to Identifier 2015–NE–33–AD; Amendment 39–
DOT Regulatory Policies and Procedures exceed 12,500 CSN. 18648; AD 2016–18–17]
(44 FR 11034, February 26, 1979), (ii) For HPC stage 8–10 spools with 11,000
CSN or more on the effective day of this AD, RIN 2120–AA64
(3) Will not affect intrastate aviation
inspect within the next 1,500 cycles in
in Alaska to the extent that it justifies service. Airworthiness Directives; Honeywell
making a regulatory distinction, and (iii) Thereafter, inspect the seal teeth of the International Inc. Turboprop and
(4) Will not have a significant HPC stage 8–10 spool at each shop visit. Turboshaft Engines
economic impact, positive or negative, (2) Remove from service any HPC stage 8–
on a substantial number of small entities 10 spool that fails the ECI or FPI required by
AGENCY: Federal Aviation
under the criteria of the Regulatory paragraph (e)(1) of this AD and replace with Administration (FAA), DOT.
Flexibility Act. a part eligible for installation. ACTION: Final rule.
(3) Guidance on performing the ECI and
List of Subjects in 14 CFR Part 39 the FPI can be found in GE Service Bulletins SUMMARY: We are adopting a new
Air transportation, Aircraft, Aviation (SBs) SB 72–1141 R00, dated December 2, airworthiness directive (AD) for certain
safety, Incorporation by reference, 2015 and SB 72–1142 R00, dated November Honeywell International Inc.
Safety. 30, 2015. (Honeywell) TPE331 model turboprop
(f) Definition engines and TSE331–3U model
Adoption of the Amendment turboshaft engines. This AD was
For the purpose of this AD, an engine shop prompted by the discovery of cracks in
Accordingly, under the authority visit is the induction of an engine into the
delegated to me by the Administrator, shop for maintenance during which the
a 2nd stage compressor impeller during
the FAA amends 14 CFR part 39 as compressor discharge pressure seal face is a routine shop visit. This AD requires
follows: exposed. removal of the 2nd stage compressor
impeller. We are issuing this AD to
PART 39—AIRWORTHINESS (g) Alternative Methods of Compliance prevent failure of the compressor
(AMOCs)
DIRECTIVES impeller, uncontained part release,
The Manager, Engine Certification Office, damage to the engine, and damage to the
■ 1. The authority citation for part 39 FAA, may approve AMOCs for this AD. Use airplane.
continues to read as follows: the procedures found in 14 CFR 39.19 to
make your request. You may email your DATES: This AD is effective November 4,
Authority: 49 U.S.C. 106(g), 40113, 44701. request to: ANE-AD-AMOC@faa.gov. 2016.
§ 39.13 [Amended] (h) Related Information Examining the AD Docket
■ 2. The FAA amends § 39.13 by adding (1) For more information about this AD, You may examine the AD docket on
the following new airworthiness contact John Frost, Aerospace Engineer, the Internet at http://
directive (AD): Engine Certification Office, FAA, 1200 www.regulations.gov by searching for
District Avenue, Burlington, MA 01803; and locating Docket No. FAA–2015–
2016–19–09 General Electric Company:
phone: 781–238–7756; fax: 781–238–7199; 4866; or in person at the Docket
Amendment 39–18658; Docket No.
email: john.frost@faa.gov.
FAA–2016–5307; Directorate Identifier Management Facility between 9 a.m.
(2) GE SB 72–1141, R00, dated December
2016–NE–08–AD.
2, 2015 and GE SB 72–1142, R00, dated and 5 p.m., Monday through Friday,
(a) Effective Date November 30, 2015, which are not except Federal holidays. The AD docket
incorporated by reference in this AD, can be contains this AD, the regulatory
This AD is effective November 4, 2016.
obtained from GE, using the contact evaluation, any comments received, and
(b) Affected ADs information in paragraph (h)(3) of this AD. other information. The address for the
None. (3) For service information identified in Docket Office (phone: 800–647–5527) is
asabaliauskas on DSK3SPTVN1PROD with RULES
this AD, contact General Electric Company, Document Management Facility, U.S.
(c) Applicability GE-Aviation, Room 285, 1 Neumann Way, Department of Transportation, Docket
This AD applies to General Electric Cincinnati, OH 45215, phone: 513–552–3272; Operations, M–30, West Building
Company (GE) GE90–76B, GE90–77B, GE90– email: aviation.fleetsupport@ge.com.
Ground Floor, Room W12–140, 1200
85B, GE90–90B, and GE90–94B turbofan (4) You may view this service information
at the FAA, Engine & Propeller Directorate, New Jersey Avenue SE., Washington,
engines with a high-pressure compressor
(HPC) stage 8–10 spool, part numbers 1200 District Avenue, Burlington, MA. For DC 20590.
1694M80G04, 1844M90G01, or 1844M90G02, information on the availability of this FOR FURTHER INFORMATION CONTACT:
installed. material at the FAA, call 781–238–7125. Joseph Costa, Aerospace Engineer, Los
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Document Created: 2018-02-09 13:34:14
Document Modified: 2018-02-09 13:34:14
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective November 4, 2016. | |
| Contact | John Frost, Aerospace Engineer, Engine Certification Office, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 81 FR 67098 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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