81 FR 4165 - Airworthiness Directives; Engine Alliance Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 16 (January 26, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 16 (January 26, 2016)
| Page Range | 4165-4167 | |
| FR Document | 2016-01268 |
[Federal Register Volume 81, Number 16 (Tuesday, January 26, 2016)] [Rules and Regulations] [Pages 4165-4167] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-01268] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3585; Directorate Identifier 2015-NE-22-AD; Amendment 39-18384; AD 2015-28-01] RIN 2120-AA64 Airworthiness Directives; Engine Alliance Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Engine Alliance (EA) GP7270 turbofan engines. This AD was prompted by the manufacturer informing us that the inspection criteria and repair procedures in the maintenance manual for aft bolt holes of the high- pressure compressor (HPC) cone shaft on the affected engines is incorrect. This AD requires inspection of the HPC cone shaft and repair of affected parts, if needed. We are issuing this AD to prevent failure of the HPC cone shaft, which could lead to uncontained engine failure and damage to the airplane. DATES: This AD is effective March 1, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 1, 2016. ADDRESSES: For service information identified in this AD, contact Engine Alliance, 400 Main St., East Hartford, CT 06108, M/S 169-10, phone: 800-565-0140; email: [email protected]; Internet: sp.engineallianceportal.com. 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. 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-2015- 3585; 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: Kyle Gustafson, Aerospace Engineer, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7183; 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 certain EA GP7270 turbofan engines. The NPRM published in the Federal Register on October 1, 2015 (80 FR 59081). The NPRM was prompted by the manufacturer informing us that the inspection criteria and repair procedures in the maintenance manual for aft bolt holes of the HPC cone shaft, also referred to as the ``HPC forward stubshaft,'' for the affected engines is incorrect. The NPRM proposed to require inspection of the HPC cone shaft and repair of affected parts, if needed. We are issuing this AD to prevent failure of the HPC cone shaft, which could lead to uncontained engine failure 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 (80 FR 59081, October 1, 2015) and the FAA's response to each comment. Request To Add Engine Models EA requested that we expand the applicability to include the GP7272 and GP7277 engine models. We disagree. There are no GP7272 or GP7277 engines in service nor have any been delivered. New engines would be delivered with corrected service [[Page 4166]] information and would not be impacted by this AD. We did not change this AD. Request To Change the Unsafe Condition Statement EA requested that the unsafe condition statement be changed from ``We are issuing this AD to prevent failure of the HPC cone shaft, which could lead to uncontained engine failure and damage to the airplane.'' to ``We are issuing this AD to prevent a hazardous engine condition.'' The reason for this request is that no HPC cone shaft failures have occurred in the field. We disagree. The unsafe condition statement describes the condition we are trying to prevent and is the justification for this AD. It does not describe what has occurred in the past. We did not change this AD. Request To Change Various Paragraphs EA requested that we revise the part nomenclature in the Applicability, Compliance, and Installation Prohibition paragraphs and in the unsafe condition statement to include both ``cone shaft'' and ``forward stubshaft.'' The part is referenced as a ``cone shaft'' in this AD and engine and component manuals; however, it is referred to as a ``forward stubshaft'' in the service bulletins (SBs). We disagree. The part nomenclature listed in the airworthiness limitations section and engine maintenance manual is ``cone shaft.'' The Discussion section of this AD explains that the terms ``cone shaft'' and ``forward stubshaft'' are synonymous. We consider including both terms throughout this AD unnecessary. We did not change this AD. Request To Revise the Compliance EA requested that the Compliance paragraph be revised to include the word ``pits'' when describing the inspection criteria. We agree. We revised paragraph (e)(1) and (f)(1) of this AD from ``. . . nicks, dents, and scratches . . .'' to ``. . . nicks, dents, pits, and scratches. . . .'' Request To Change the Compliance EA requested that we replace ``Do not reinstall the HPC cone shaft if the aft bolt hole has a nick, dent, or scratch that is greater than 0.002 inch in depth'' in paragraph (e)(1) of this AD with ``Comply with the Accomplishment Instructions in EA SB No. EAGP7-72-330 if the aft bolt hole has a nick, dent, pit, or scratch that is greater than the serviceable limit.'' We disagree. The current engine manual has an approved repair procedure for damage that is more severe than the installation requirements of this AD. It is not necessary to restate what is already allowed by the engine manual. We did not change this AD. Request To Change Service Information EA requested that the phrase ``or later'' be used when referring to SBs. We disagree. We are only authorized to mandate use of SBs that we have reviewed and which are published. Since future revisions of SBs are not yet published, we are not authorized to mandate their use. We did not change this AD. Request To Change the Installation Prohibition EA requested that we change the Installation Prohibition paragraph to read: ``After the effective date of this AD, do not install an HPC cone shaft onto an engine: (1) that has accumulated more than 9,000 cycles since new that has not complied with this AD on an applicable part, and (2) has a nick, dent, or scratch in an HPC cone shaft aft bolt hole that is greater than the serviceable limit.'' We disagree. The intent of the Installation Prohibition paragraph is to mandate the new serviceable limit of 0.002 inch for damage to the inner diameter of the bolt holes for the entire GP7270 fleet. Any parts with damage beyond this limit may be repaired using the approved procedures listed in the engine manual, provided that you include shot peening as required by paragraph (f)(2) of this AD. 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 with the changes described previously. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 EA has issued SB No. EAGP7-72-329, dated July 21, 2015 and SB No. EAGP7-72-330, dated July 21, 2015. The service information describes procedures for shotpeening the HPC forward stubshaft and inspecting the HPC forward stubshaft bolt-hole inner diameter respectively. 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 of this final rule. Costs of Compliance We estimate that this AD affects zero engines installed on airplanes of U.S. registry. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $0. 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 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: [[Page 4167]] 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): 2015-28-01 Engine Alliance: Amendment 39-18384; Docket No. FAA-2015- 3585; Directorate Identifier 2015-NE-22-AD. (a) Effective Date This AD is effective March 1, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Engine Alliance (EA) GP7270 turbofan engines with a high-pressure compressor (HPC) cone shaft, part number 382- 100-907-0, installed. (d) Unsafe Condition This AD was prompted by the manufacturer informing us that the inspection and repair criteria in the maintenance manual for aft bolt holes of the HPC cone shaft on the affected engines is incorrect. We are issuing this AD to prevent failure of the HPC cone shaft, which could lead to uncontained engine failure and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For HPC cone shafts with serial numbers listed in EA Service Bulletin (SB) No. EAGP7-72-330, dated July 21, 2015, inspect the inner diameter of the HPC cone shaft aft bolt holes for nicks, dents, pits, and scratches before accumulating 9,000 cycles since new (CSN). Do not reinstall the HPC cone shaft if the aft bolt hole has any nicks, dents, pits, or scratches that are greater than 0.002 inch in depth. (2) For HPC cone shafts with serial numbers listed in EA SB No. EAGP7-72-329, dated July 21, 2015, shot peen the HPC cone shaft aft bolt holes before accumulating 9,000 CSN. Use paragraph 1 of the Accomplishment Instructions in EA SB No. EAGP7-72-329 to do the shot peening. (f) Installation Prohibition After the effective date of this AD, do not install an HPC cone shaft on any engine with the following: (1) any nicks, dents, pits, or scratches in an HPC cone shaft aft bolt hole that is greater than 0.002 inch in depth; or (2) any repair of an HPC cone shaft aft bolt hole that did not include shot peening. (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, 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 For more information about this AD, contact Kyle Gustafson, Aerospace Engineer, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7183; fax: 781-238-7199; email: [email protected]. (i) 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) Engine Alliance (EA) Service Bulletin (SB) No. EAGP7-72-329, dated July 21, 2015. (ii) EA SB No. EAGP7-72-330, dated July 21, 2015. (3) For EA service information identified in this AD, contact Engine Alliance, 400 Main St., East Hartford, CT 06108, M/S 169-10; phone: 800-565-0140; email: [email protected]; Internet: sp.engineallianceportal.com. (4) You may view this service information at FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (5) You may view this service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on January 13, 2016. Gaetano Sciortino, Acting Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-01268 Filed 1-25-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 4165
requested using the procedures found in 14 (5) You may view this service information Burlington, MA. For information on the
CFR 39.19. In accordance with 14 CFR 39.19, at FAA, Transport Airplane Directorate, 1601 availability of this material at the FAA,
send your request to your principal inspector Lind Avenue SW., Renton, WA. For call 781–238–7125.
or local Flight Standards District Office, as information on the availability of this
appropriate. If sending information directly material at the FAA, call 425–227–1221. Examining the AD Docket
to the manager of the ACO, send it to the (6) You may view this service information
attention of the person identified in that is incorporated by reference at the
You may examine the AD docket on
paragraph (j) of this AD. Information may be National Archives and Records the Internet at http://
emailed to: 9–ANM-Seattle-ACO–AMOC- Administration (NARA). For information on www.regulations.gov by searching for
Requests@faa.gov. the availability of this material at NARA, call and locating Docket No. FAA–2015–
(2) Before using any approved AMOC, 202–741–6030, or go to: http://www.archives. 3585; or in person at the Docket
notify your appropriate principal inspector, gov/federal-register/cfr/ibr-locations.html. Management Facility between 9 a.m.
or lacking a principal inspector, the manager and 5 p.m., Monday through Friday,
of the local flight standards district office/ Issued in Renton, Washington, on January except Federal holidays. The AD docket
certificate holding district office. 19, 2016.
(3) An AMOC that provides an acceptable
contains this AD, the regulatory
Michael Kaszycki, evaluation, any comments received, and
level of safety may be used for any repair,
modification, or alteration required by this Acting Manager, Transport Airplane other information. The address for the
AD if it is approved by the Boeing Directorate, Aircraft Certification Service. Docket Office (phone: 800–647–5527) is
Commercial Airplanes Organization [FR Doc. 2016–01441 Filed 1–25–16; 8:45 am] Document Management Facility, U.S.
Designation Authorization (ODA) that has BILLING CODE 4910–13–P Department of Transportation, Docket
been authorized by the Manager, Seattle Operations, M–30, West Building
ACO, to make those findings. To be Ground Floor, Room W12–140, 1200
approved, the repair method, modification DEPARTMENT OF TRANSPORTATION New Jersey Avenue SE., Washington,
deviation, or alteration deviation must meet
the certification basis of the airplane and the DC 20590.
Federal Aviation Administration
approval must specifically refer to this AD. FOR FURTHER INFORMATION CONTACT: Kyle
(4) For service information that contains Gustafson, Aerospace Engineer, Engine
steps that are labeled as Required for 14 CFR Part 39
& Propeller Directorate, FAA, 1200
Compliance (RC), the provisions of [Docket No. FAA–2015–3585; Directorate District Avenue, Burlington, MA 01803;
paragraphs (i)(4)(i) and (i)(4)(ii) of this AD Identifier 2015–NE–22–AD; Amendment 39– phone: 781–238–7183; fax: 781–238–
apply. 18384; AD 2015–28–01] 7199; email: kyle.gustafson@faa.gov.
(i) The steps labeled as RC, including
substeps under an RC step and any figures RIN 2120–AA64 SUPPLEMENTARY INFORMATION:
identified in an RC step, must be done to Discussion
comply with the AD. An AMOC is required Airworthiness Directives; Engine
for any deviations to RC steps, including Alliance Turbofan Engines We issued a notice of proposed
substeps and identified figures. rulemaking (NPRM) to amend 14 CFR
(ii) Steps not labeled as RC may be AGENCY: Federal Aviation part 39 by adding an AD that would
deviated from using accepted methods in Administration (FAA), DOT. apply to certain EA GP7270 turbofan
accordance with the operator’s maintenance ACTION: Final rule. engines. The NPRM published in the
or inspection program without obtaining
approval of an AMOC, provided the RC steps, SUMMARY: We are adopting a new Federal Register on October 1, 2015 (80
including substeps and identified figures, can airworthiness directive (AD) for certain FR 59081). The NPRM was prompted by
still be done as specified, and the airplane Engine Alliance (EA) GP7270 turbofan the manufacturer informing us that the
can be put back in an airworthy condition. engines. This AD was prompted by the inspection criteria and repair
manufacturer informing us that the procedures in the maintenance manual
(j) Related Information
inspection criteria and repair for aft bolt holes of the HPC cone shaft,
For more information about this AD, also referred to as the ‘‘HPC forward
contact Eric Lin, Aerospace Engineer, procedures in the maintenance manual
for aft bolt holes of the high-pressure stubshaft,’’ for the affected engines is
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA compressor (HPC) cone shaft on the incorrect. The NPRM proposed to
98057–3356; phone: 425–917–6412; fax: 425– affected engines is incorrect. This AD require inspection of the HPC cone shaft
917–6590; email: Eric.Lin@faa.gov. requires inspection of the HPC cone and repair of affected parts, if needed.
shaft and repair of affected parts, if We are issuing this AD to prevent
(k) Material Incorporated by Reference
needed. We are issuing this AD to failure of the HPC cone shaft, which
(1) The Director of the Federal Register could lead to uncontained engine failure
approved the incorporation by reference prevent failure of the HPC cone shaft,
which could lead to uncontained engine and damage to the airplane.
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR failure and damage to the airplane. Comments
part 51. DATES: This AD is effective March 1,
(2) You must use this service information We gave the public the opportunity to
2016. participate in developing this AD. The
as applicable to do the actions required by The Director of the Federal Register
this AD, unless the AD specifies otherwise. following presents the comments
(3) The following service information was
approved the incorporation by reference received on the NPRM (80 FR 59081,
approved for IBR on January 28, 2016 (80 FR of a certain publication listed in this AD October 1, 2015) and the FAA’s
80234, December 24, 2015). as of March 1, 2016. response to each comment.
(i) Boeing Alert Service Bulletin 777– ADDRESSES: For service information
53A0078, dated December 5, 2014. identified in this AD, contact Engine Request To Add Engine Models
mstockstill on DSK4VPTVN1PROD with RULES
(ii) Reserved. Alliance, 400 Main St., East Hartford, EA requested that we expand the
(4) For service information identified in CT 06108, M/S 169–10, phone: 800– applicability to include the GP7272 and
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
565–0140; email: help24@pw.utc.com; GP7277 engine models.
Management, P. O. Box 3707, MC 2H–65, Internet: sp.engineallianceportal.com. We disagree. There are no GP7272 or
Seattle, WA 98124–2207; telephone 206– You may view this service information GP7277 engines in service nor have any
544–5000, extension 1; fax 206 766 5680; at the FAA, Engine & Propeller been delivered. New engines would be
Internet https://www.myboeingfleet.com. Directorate, 1200 District Avenue, delivered with corrected service
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![Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 4167
PART 39—AIRWORTHINESS your request. You may email your request to: This AD was prompted by a report that
DIRECTIVES ANE–AD–AMOC@faa.gov. the aft mount pylon bolts of the CFM56–
(h) Related Information 5 engines may have been installed using
■ 1. The authority citation for part 39 the wrong torque values. This AD
For more information about this AD,
continues to read as follows: contact Kyle Gustafson, Aerospace Engineer, requires identification of engines that
Authority: 49 U.S.C. 106(g), 40113, 44701. Engine & Propeller Directorate, FAA, 1200 were installed using the wrong torque
District Avenue, Burlington, MA 01803; values and re-torque of the four aft
§ 39.13 [Amended] phone: 781–238–7183; fax: 781–238–7199; mount pylon bolts of those engines. We
■ 2. The FAA amends § 39.13 by adding email: kyle.gustafson@faa.gov. are issuing this AD to detect and correct
the following new airworthiness (i) Material Incorporated by Reference improper torque of the aft mount pylon
directive (AD): bolts, which, if combined with any
(1) The Director of the Federal Register
2015–28–01 Engine Alliance: Amendment approved the incorporation by reference maintenance damage, could lead to aft
39–18384; Docket No. FAA–2015–3585; (IBR) of the service information listed in this engine mount failure, possibly resulting
Directorate Identifier 2015–NE–22–AD. paragraph under 5 U.S.C. 552(a) and 1 CFR in engine detachment and consequent
(a) Effective Date
part 51. reduced control of the airplane.
(2) You must use this service information DATES: This AD becomes effective
This AD is effective March 1, 2016. as applicable to do the actions required by March 1, 2016.
this AD, unless the AD specifies otherwise.
(b) Affected ADs The Director of the Federal Register
(i) Engine Alliance (EA) Service Bulletin
None. (SB) No. EAGP7–72–329, dated July 21, 2015. approved the incorporation by reference
(ii) EA SB No. EAGP7–72–330, dated July of a certain publication listed in this AD
(c) Applicability
21, 2015. as of March 1, 2016.
This AD applies to Engine Alliance (EA) (3) For EA service information identified in ADDRESSES: You may examine the AD
GP7270 turbofan engines with a high- this AD, contact Engine Alliance, 400 Main
pressure compressor (HPC) cone shaft, part
docket on the Internet at http://www.
St., East Hartford, CT 06108, M/S 169–10; regulations.gov/#!docketDetail;D=FAA–
number 382–100–907–0, installed. phone: 800–565–0140; email: help24@
2015–1429; or in person at the Docket
(d) Unsafe Condition pw.utc.com; Internet:
sp.engineallianceportal.com. Management Facility, U.S. Department
This AD was prompted by the (4) You may view this service information of Transportation, Docket Operations,
manufacturer informing us that the at FAA, Engine & Propeller Directorate, 1200 M–30, West Building Ground Floor,
inspection and repair criteria in the District Avenue, Burlington, MA. For Room W12–140, 1200 New Jersey
maintenance manual for aft bolt holes of the information on the availability of this Avenue SE., Washington, DC.
HPC cone shaft on the affected engines is material at the FAA, call 781–238–7125. For service information identified in
incorrect. We are issuing this AD to prevent (5) You may view this service information
failure of the HPC cone shaft, which could
this final rule, contact Airbus,
at the National Archives and Records Airworthiness Office—EIAS, 1 Rond
lead to uncontained engine failure and Administration (NARA). For information on
damage to the airplane. Point Maurice Bellonte, 31707 Blagnac
the availability of this material at NARA, call
202–741–6030, or go to: http://www.archives.
Cedex, France; telephone: +33 5 61 93
(e) Compliance 36 96; fax: +33 5 61 93 44 51; email:
gov/federal-register/cfr/ibr-locations.html.
Comply with this AD within the account.airworth-eas@airbus.com;
compliance times specified, unless already Issued in Burlington, Massachusetts, on Internet http://www.airbus.com. You
done. January 13, 2016.
may view this referenced service
(1) For HPC cone shafts with serial Gaetano Sciortino,
numbers listed in EA Service Bulletin (SB)
information at the FAA, Transport
Acting Directorate Manager, Engine & Airplane Directorate, 1601 Lind Avenue
No. EAGP7–72–330, dated July 21, 2015, Propeller Directorate, Aircraft Certification
inspect the inner diameter of the HPC cone SW., Renton, WA. For information on
Service.
shaft aft bolt holes for nicks, dents, pits, and the availability of this material at the
[FR Doc. 2016–01268 Filed 1–25–16; 8:45 am]
scratches before accumulating 9,000 cycles FAA, call 425–227–1221. It is also
since new (CSN). Do not reinstall the HPC BILLING CODE 4910–13–P available on the Internet at http://
cone shaft if the aft bolt hole has any nicks, www.regulations.gov by searching for
dents, pits, or scratches that are greater than and locating Docket No. FAA–2015–
0.002 inch in depth. DEPARTMENT OF TRANSPORTATION 1429.
(2) For HPC cone shafts with serial
numbers listed in EA SB No. EAGP7–72–329, Federal Aviation Administration FOR FURTHER INFORMATION CONTACT:
dated July 21, 2015, shot peen the HPC cone Sanjay Ralhan, Aerospace Engineer,
shaft aft bolt holes before accumulating 9,000 14 CFR Part 39 International Branch, ANM–116,
CSN. Use paragraph 1 of the Transport Airplane Directorate, FAA,
Accomplishment Instructions in EA SB No. [Docket No. FAA–2015–1429; Directorate
Identifier 2014–NM–246–AD; Amendment 1601 Lind Avenue SW., Renton, WA
EAGP7–72–329 to do the shot peening. 98057–3356; telephone: 425–227–1405;
39–18382; AD 2016–02–03]
(f) Installation Prohibition fax: 425–227–1149.
RIN 2120–AA64
After the effective date of this AD, do not Discussion
install an HPC cone shaft on any engine with
Airworthiness Directives; Airbus We issued a notice of proposed
the following:
(1) any nicks, dents, pits, or scratches in an Airplanes rulemaking (NPRM) to amend 14 CFR
HPC cone shaft aft bolt hole that is greater AGENCY: Federal Aviation part 39 by adding an AD that would
than 0.002 inch in depth; or Administration (FAA), Department of apply to certain Airbus Model A319–
mstockstill on DSK4VPTVN1PROD with RULES
(2) any repair of an HPC cone shaft aft bolt 113, A319–114, A320–211, and A320–
Transportation (DOT).
hole that did not include shot peening. 212 airplanes. The NPRM published in
ACTION: Final rule.
(g) Alternative Methods of Compliance the Federal Register on June 15, 2015
(AMOCs) SUMMARY: We are adopting a new (80 FR 34101). The NPRM was
The Manager, Engine Certification Office, airworthiness directive (AD) for certain prompted by a report that the aft mount
may approve AMOCs for this AD. Use the Airbus Model A319–113, A319–114, pylon bolts of the CFM56–5 engines
procedures found in 14 CFR 39.19 to make A320–211, and A320–212 airplanes. may have been installed using the
VerDate Sep<11>2014 16:44 Jan 25, 2016 Jkt 238001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\26JAR1.SGM 26JAR1](https://thefederalregister.org/doc/81_FR_4181/page/3.svg)
Document Created: 2018-02-02 12:37:48
Document Modified: 2018-02-02 12:37:48
| 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 March 1, 2016. | |
| Contact | Kyle Gustafson, Aerospace Engineer, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7183; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 81 FR 4165 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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