81 FR 75684 - Airworthiness Directives; Engine Alliance Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 211 (November 1, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 211 (November 1, 2016)
| Page Range | 75684-75686 | |
| FR Document | 2016-26280 |
[Federal Register Volume 81, Number 211 (Tuesday, November 1, 2016)] [Rules and Regulations] [Pages 75684-75686] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-26280] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2012-1293; Directorate Identifier 2012-NE-45-AD; Amendment 39-18700; AD 2016-22-11] RIN 2120-AA64 Airworthiness Directives; Engine Alliance Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are superseding airworthiness directive (AD) 2013-02-06 for all Engine Alliance (EA) GP7270 and GP7277 turbofan engines with certain part number (P/N) high-pressure turbine (HPT) stage 2 nozzle segments installed. AD 2013-02-06 required initial and repetitive borescope inspections (BSI) and removal from service of these nozzles before further flight if one or more burn holes were detected in any HPT stage 2 nozzle segment. AD 2013-02-06 also required removal from service of these HPT stage 2 nozzle segments at the next engine shop visit. This AD requires the same inspections as AD-2013-02-06, requires removal of affected HPT stage 2 nozzles at next piece-part exposure, and adds certain P/Ns to the applicability. This AD was prompted by another report of inadequate cooling of the HPT stage 1 shroud and stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn- through of the turbine case, and in-flight shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure, uncontrolled fire, in- flight shutdown, and damage to the airplane. DATES: This AD is effective November 16, 2016. We must receive any comments on this AD by December 16, 2016. 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 http://www.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: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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-2012- 1293; 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 street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Martin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7157; fax: 781-238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion On January 15, 2013, we issued AD 2013-02-06, Amendment 39-17327 (78 FR 5710, January 28, 2013), (``AD 2013-02-06''), for all Engine Alliance GP7270 and GP7277 turbofan engines with an HPT stage 2 nozzle, P/N 2101M24G01, 2101M24G02, or 2101M24G03, installed. AD 2013-02-06 required initial and repetitive BSIs and removal from service of these nozzles before further flight if any burn holes were detected in the affected nozzles. AD 2013-02-06 also required removal from service of the affected nozzles at the next engine shop visit. AD 2013-02-06 resulted from a report of inadequate cooling of the HPT stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and in-flight shutdown. We issued AD 2013-02-06 to prevent HPT stage 2 nozzle failure, uncontrolled fire, in-flight shutdown, and damage to the airplane. Actions Since AD 2013-02-06 Was Issued Since we issued AD 2013-02-06, we received another report of inadequate cooling of the HPT stage 1 shroud and stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and in-flight shutdown. This event occurred with HPT stage 2 nozzle, P/N 2101M24G04, 2101M24G05, or 2101M24G06 installed. Investigation revealed that the event was caused by damage to the HPT stage 2 nozzle due to inadequate part cooling. We are issuing this AD to prevent HPT stage 2 nozzle failure, uncontrolled fire, in-flight shutdown, and damage to the airplane. Related Service Information We reviewed EA Service Bulletins EAGP7-72-190, dated December 6, 2012 and EAGP7-72-262, Revision No. 5, dated December 18, 2015. This service information describes procedures for inspecting the HPT stage 2 nozzle segments. FAA's Determination We are issuing this AD because we 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. AD Requirements This AD requires initial and repetitive BSIs of the HPT stage 1 shroud and HPT [[Page 75685]] stage 2 nozzle segments and removal from service of these nozzle segments before further flight if one or more burn holes are detected on the HPT stage 2 nozzle or if the HPT stage 1 shroud is found distorted. This AD also requires removal from service of any HPT stage 2 nozzle segment, P/N 2101M24G01, 2101M24G02, 2101M24G03, 2101M24G04, 2101M24G05, or 2101M24G06, at next piece-part exposure. FAA's Justification and Determination of the Effective Date No domestic operators use this product. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA-2012-1293 and Directorate Identifier 2012-NE-45- AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD will affect no engines installed on airplanes of U.S. registry. We also estimate that it will take about two hours per engine to perform a BSI of the HPT stage 2 nozzle. The average labor rate is $85 per hour. Required parts cost about $504,486 per engine. Based on these figures, we estimate the cost of this AD to 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 part 39 of the Federal Aviation Regulations (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 removing airworthiness directive (AD) 2013-02-06, Amendment 39-17327 (78 FR 5710, January 28, 2013) and adding the following new AD: 2016-22-11 Engine Alliance: Amendment 39-18700; Docket No. FAA-2012- 1293; Directorate Identifier 2012-NE-45-AD. (a) Effective Date This AD is effective November 16, 2016. (b) Affected ADs This AD replaces AD 2013-02-06, Amendment 39-17327 (78 FR 5710, January 28, 2013). (c) Applicability This AD applies to all Engine Alliance GP7270 and GP7277 turbofan engines with a high-pressure turbine (HPT) stage 2 nozzle segment, part number (P/N) 2101M24G01, 2101M24G02, 2101M24G03, 2101M24G04, 2101M24G05, or 2101M24G06, installed. (d) Unsafe Condition This AD was prompted by a report of inadequate cooling of the HPT stage 1 shroud and stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and in-flight shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure, uncontrolled fire, in-flight shutdown, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Perform a 360 degree borescope inspection of the HPT stage 1 shroud and stage 2 nozzle as follows: (i) For engines with nozzles installed at a shop visit that did not include full engine overhaul, borescope inspect the HPT stage 1 shroud and stage 2 nozzle as follows: (A) If the nozzle has fewer than 1,050 cycles-since-new (CSN) or cycles-since-repair (CSR) on the effective date of this AD, before the nozzle has accumulated 1,100 CSN or CSR. (B) If the nozzle has 1,050 or more CSN or CSR on the effective date of this AD, within the next 50 cycles. (ii) For all other engines, borescope inspect the HPT stage 1 shroud and HPT stage 2 nozzle as follows: (A) If the nozzle has fewer than 1,450 CSN or CSR on the effective date of this AD, before the nozzle has accumulated 1,500 CSN or CSR. (B) If the nozzle has 1,450 or more CSN or CSR on the effective date of this AD, within the next 50 cycles. (iii) Thereafter, repetitively borescope inspect the HPT stage 1 shroud and stage 2 nozzle as follows: (A) For engines with HPT stage 2 nozzle segments, P/N 2101M24G01, 2101M24G02, or 2101M24G03, within every 150 additional cycles-in-service (CIS). (B) For engines with HPT stage 2 nozzle segments, P/N 2101M24G04, 2101M24G05, or 2101M24G06, within every 300 additional CIS. (2) If any burn holes are detected through the surface of the nozzle or if the shroud is distorted radially inward with evidence of blade tip rubs, remove the HPT stage 1 shroud and HPT stage 2 nozzle from service before further flight. [[Page 75686]] (f) Mandatory Terminating Action Replace HPT stage 2 nozzle segments, P/N 2101M24G01, 2101M24G02, 2101M24G03, 2101M24G04, 2101M24G05, and 2101M24G06, at the next piece-part exposure, with parts eligible for installation. (g) Definition For the purpose of this AD, piece-part exposure is when the HPT stage 2 nozzle is removed from the engine and completely disassembled. (h) 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]. (i) Related Information For more information about this AD, contact Martin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7157; fax: 781-238-7199; email: [email protected]. (j) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on October 25, 2016. Colleen M. D'Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-26280 Filed 10-31-16; 8:45 am] BILLING CODE 4910-13-P
![75684 Federal Register / Vol. 81, No. 211 / Tuesday, November 1, 2016 / Rules and Regulations
criteria. In addition to utilizing these installed. AD 2013–02–06 required 01803; phone: 781–238–7157; fax: 781–
selection criteria, when a contracting initial and repetitive borescope 238–7199; email: martin.adler@faa.gov.
agency enters into a contract both for inspections (BSI) and removal from SUPPLEMENTARY INFORMATION:
the processing of donated food and the service of these nozzles before further
purchase of the end products produced flight if one or more burn holes were Discussion
from the donated food, the procurement detected in any HPT stage 2 nozzle On January 15, 2013, we issued AD
standards set forth in 2 CFR part 200, segment. AD 2013–02–06 also required 2013–02–06, Amendment 39–17327 (78
subpart D and Appendix II, Contract removal from service of these HPT stage FR 5710, January 28, 2013), (‘‘AD 2013–
Provisions for Non-Federal Entity 2 nozzle segments at the next engine 02–06’’), for all Engine Alliance GP7270
Contracts Under Federal Awards and shop visit. This AD requires the same and GP7277 turbofan engines with an
USDA implementing regulations at 2 inspections as AD–2013–02–06, requires HPT stage 2 nozzle, P/N 2101M24G01,
CFR part 400 and part 416 must be removal of affected HPT stage 2 nozzles 2101M24G02, or 2101M24G03,
followed. Recipient agencies which at next piece-part exposure, and adds installed. AD 2013–02–06 required
purchase end products produced under certain P/Ns to the applicability. This initial and repetitive BSIs and removal
Statewide agreements are also required AD was prompted by another report of from service of these nozzles before
to comply with 2 CFR part 200, subpart inadequate cooling of the HPT stage 1 further flight if any burn holes were
D and USDA implementing regulations shroud and stage 2 nozzle, leading to detected in the affected nozzles. AD
at 2 CFR part 400 and part 416. damage to the HPT stage 2 nozzle, burn- 2013–02–06 also required removal from
Contracting agencies shall not enter into through of the turbine case, and in-flight service of the affected nozzles at the
contracts with processors which cannot shutdown. We are issuing this AD to next engine shop visit. AD 2013–02–06
demonstrate the ability to meet the prevent HPT stage 2 nozzle failure, resulted from a report of inadequate
terms and conditions of the regulations uncontrolled fire, in-flight shutdown, cooling of the HPT stage 2 nozzle,
and the distributing agency agreements; and damage to the airplane. leading to damage to the HPT stage 2
furnish prior to the delivery of any DATES: This AD is effective November nozzle, burn-through of the turbine case,
donated foods for processing, a 16, 2016. and in-flight shutdown. We issued AD
performance bond, an irrevocable letter We must receive any comments on 2013–02–06 to prevent HPT stage 2
of credit or an escrow account in an this AD by December 16, 2016. nozzle failure, uncontrolled fire, in-
amount sufficient to protect the contract ADDRESSES: You may send comments, flight shutdown, and damage to the
value of donated food on hand and on using the procedures found in 14 CFR airplane.
order; demonstrate the ability to 11.43 and 11.45, by any of the following Actions Since AD 2013–02–06 Was
distribute end products to eligible methods: Issued
recipient agencies; provide a satisfactory • Federal eRulemaking Portal: Go to
record of integrity, business ethics and Since we issued AD 2013–02–06, we
http://www.regulations.gov. Follow the
performance and provide adequate received another report of inadequate
instructions for submitting comments.
storage. cooling of the HPT stage 1 shroud and
• Fax: 202–493–2251.
stage 2 nozzle, leading to damage to the
* * * * * • Mail: U.S. Department of
HPT stage 2 nozzle, burn-through of the
Dated: October 24, 2016. Transportation, Docket Operations, M–
turbine case, and in-flight shutdown.
Telora T. Dean, 30, West Building Ground Floor, Room
This event occurred with HPT stage 2
Acting Administrator, Food and Nutrition
W12–140, 1200 New Jersey Avenue SE.,
nozzle, P/N 2101M24G04, 2101M24G05,
Service. Washington, DC 20590.
• Hand Delivery: U.S. Department of or 2101M24G06 installed. Investigation
[FR Doc. 2016–26329 Filed 10–31–16; 8:45 am]
Transportation, Docket Operations, M– revealed that the event was caused by
BILLING CODE 3410–30–P
30, West Building Ground Floor, Room damage to the HPT stage 2 nozzle due
W12–140, 1200 New Jersey Avenue SE., to inadequate part cooling. We are
Washington, DC 20590, between 9 a.m. issuing this AD to prevent HPT stage 2
DEPARTMENT OF TRANSPORTATION and 5 p.m., Monday through Friday, nozzle failure, uncontrolled fire, in-
except Federal holidays. flight shutdown, and damage to the
Federal Aviation Administration airplane.
Examining the AD Docket
14 CFR Part 39 Related Service Information
You may examine the AD docket on
We reviewed EA Service Bulletins
[Docket No. FAA–2012–1293; Directorate the Internet at http://
Identifier 2012–NE–45–AD; Amendment 39– EAGP7–72–190, dated December 6,
www.regulations.gov by searching for
18700; AD 2016–22–11] 2012 and EAGP7–72–262, Revision No.
and locating Docket No. FAA–2012–
5, dated December 18, 2015. This
RIN 2120–AA64 1293; or in person at the Docket
service information describes
Management Facility between 9 a.m.
Airworthiness Directives; Engine procedures for inspecting the HPT stage
and 5 p.m., Monday through Friday,
Alliance Turbofan Engines 2 nozzle segments.
except Federal holidays. The AD docket
AGENCY: Federal Aviation contains this AD, the regulatory FAA’s Determination
Administration (FAA), DOT. evaluation, any comments received, and We are issuing this AD because we
other information. The street address for evaluated all the relevant information
ACTION: Final rule; request for
the Docket Office (phone: 800–647– and determined the unsafe condition
comments.
jstallworth on DSK7TPTVN1PROD with RULES
5527) is in the ADDRESSES section. described previously is likely to exist or
SUMMARY: We are superseding Comments will be available in the AD develop in other products of the same
airworthiness directive (AD) 2013–02– docket shortly after receipt. type design.
06 for all Engine Alliance (EA) GP7270 FOR FURTHER INFORMATION CONTACT:
and GP7277 turbofan engines with Martin Adler, Aerospace Engineer, AD Requirements
certain part number (P/N) high-pressure Engine & Propeller Directorate, FAA, This AD requires initial and repetitive
turbine (HPT) stage 2 nozzle segments 1200 District Avenue, Burlington, MA BSIs of the HPT stage 1 shroud and HPT
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![Federal Register / Vol. 81, No. 211 / Tuesday, November 1, 2016 / Rules and Regulations 75685
stage 2 nozzle segments and removal Aviation Programs, describes in more 2016–22–11 Engine Alliance: Amendment
from service of these nozzle segments detail the scope of the Agency’s 39–18700; Docket No. FAA–2012–1293;
before further flight if one or more burn authority. Directorate Identifier 2012–NE–45–AD.
holes are detected on the HPT stage 2 We are issuing this rulemaking under (a) Effective Date
nozzle or if the HPT stage 1 shroud is the authority described in Subtitle VII,
This AD is effective November 16, 2016.
found distorted. This AD also requires Part A, Subpart III, Section 44701,
removal from service of any HPT stage ‘‘General requirements.’’ Under that (b) Affected ADs
2 nozzle segment, P/N 2101M24G01, section, Congress charges the FAA with This AD replaces AD 2013–02–06,
2101M24G02, 2101M24G03, promoting safe flight of civil aircraft in Amendment 39–17327 (78 FR 5710, January
2101M24G04, 2101M24G05, or air commerce by prescribing regulations 28, 2013).
2101M24G06, at next piece-part for practices, methods, and procedures (c) Applicability
exposure. the Administrator finds necessary for
This AD applies to all Engine Alliance
safety in air commerce. This regulation
FAA’s Justification and Determination GP7270 and GP7277 turbofan engines with a
is within the scope of that authority high-pressure turbine (HPT) stage 2 nozzle
of the Effective Date because it addresses an unsafe condition segment, part number (P/N) 2101M24G01,
No domestic operators use this that is likely to exist or develop on 2101M24G02, 2101M24G03, 2101M24G04,
product. Therefore, we find that notice products identified in this rulemaking 2101M24G05, or 2101M24G06, installed.
and opportunity for prior public action.
(d) Unsafe Condition
comment are unnecessary and that good Regulatory Findings
cause exists for making this amendment This AD was prompted by a report of
effective in less than 30 days. This AD will not have federalism inadequate cooling of the HPT stage 1 shroud
implications under Executive Order and stage 2 nozzle, leading to damage to the
Comments Invited 13132. This AD will not have a HPT stage 2 nozzle, burn-through of the
substantial direct effect on the States, on turbine case, and in-flight shutdown. We are
This AD is a final rule that involves
issuing this AD to prevent HPT stage 2 nozzle
requirements affecting flight safety, and the relationship between the national
failure, uncontrolled fire, in-flight shutdown,
we did not provide you with notice and government and the States, or on the and damage to the airplane.
an opportunity to provide your distribution of power and
comments before it becomes effective. responsibilities among the various (e) Compliance
However, we invite you to send any levels of government. Comply with this AD within the
written data, views, or arguments about For the reasons discussed above, I compliance times specified, unless already
this AD. Send your comments to an certify that this AD: done.
address listed under the ADDRESSES (1) Is not a ‘‘significant regulatory (1) Perform a 360 degree borescope
action’’ under Executive Order 12866, inspection of the HPT stage 1 shroud and
section. Include the docket number stage 2 nozzle as follows:
FAA–2012–1293 and Directorate (2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures (i) For engines with nozzles installed at a
Identifier 2012–NE–45–AD at the shop visit that did not include full engine
beginning of your comments. We (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation overhaul, borescope inspect the HPT stage 1
specifically invite comments on the shroud and stage 2 nozzle as follows:
in Alaska to the extent that it justifies
overall regulatory, economic, (A) If the nozzle has fewer than 1,050
making a regulatory distinction, and cycles-since-new (CSN) or cycles-since-repair
environmental, and energy aspects of (4) Will not have a significant
this AD. We will consider all comments (CSR) on the effective date of this AD, before
economic impact, positive or negative, the nozzle has accumulated 1,100 CSN or
received by the closing date and may on a substantial number of small entities CSR.
amend this AD because of those under the criteria of the Regulatory (B) If the nozzle has 1,050 or more CSN or
comments. Flexibility Act. CSR on the effective date of this AD, within
We will post all comments we the next 50 cycles.
receive, without change, to http:// List of Subjects in 14 CFR Part 39 (ii) For all other engines, borescope inspect
www.regulations.gov, including any Air transportation, Aircraft, Aviation the HPT stage 1 shroud and HPT stage 2
personal information you provide. We safety, Incorporation by reference, nozzle as follows:
will also post a report summarizing each Safety. (A) If the nozzle has fewer than 1,450 CSN
substantive verbal contact we receive or CSR on the effective date of this AD,
about this AD. Adoption of the Amendment before the nozzle has accumulated 1,500 CSN
Accordingly, under the authority or CSR.
Costs of Compliance (B) If the nozzle has 1,450 or more CSN or
delegated to me by the Administrator, CSR on the effective date of this AD, within
We estimate that this AD will affect the FAA amends part 39 of the Federal the next 50 cycles.
no engines installed on airplanes of U.S. Aviation Regulations (14 CFR part 39) as (iii) Thereafter, repetitively borescope
registry. We also estimate that it will follows: inspect the HPT stage 1 shroud and stage 2
take about two hours per engine to nozzle as follows:
perform a BSI of the HPT stage 2 nozzle. PART 39—AIRWORTHINESS (A) For engines with HPT stage 2 nozzle
The average labor rate is $85 per hour. DIRECTIVES segments, P/N 2101M24G01, 2101M24G02,
Required parts cost about $504,486 per or 2101M24G03, within every 150 additional
engine. Based on these figures, we ■ 1. The authority citation for part 39 cycles-in-service (CIS).
estimate the cost of this AD to U.S. continues to read as follows: (B) For engines with HPT stage 2 nozzle
operators to be $0. Authority: 49 U.S.C. 106(g), 40113, 44701. segments, P/N 2101M24G04, 2101M24G05,
jstallworth on DSK7TPTVN1PROD with RULES
or 2101M24G06, within every 300 additional
Authority for This Rulemaking § 39.13 [Amended] CIS.
(2) If any burn holes are detected through
Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by the surface of the nozzle or if the shroud is
specifies the FAA’s authority to issue removing airworthiness directive (AD) distorted radially inward with evidence of
rules on aviation safety. Subtitle I, 2013–02–06, Amendment 39–17327 (78 blade tip rubs, remove the HPT stage 1
Section 106, describes the authority of FR 5710, January 28, 2013) and adding shroud and HPT stage 2 nozzle from service
the FAA Administrator. Subtitle VII, the following new AD: before further flight.
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(f) Mandatory Terminating Action prevent failure of the fuel nozzles, replacement with parts eligible for
Replace HPT stage 2 nozzle segments, P/N which could lead to engine fire and installation. We are issuing this AD to
2101M24G01, 2101M24G02, 2101M24G03, damage to the airplane. prevent failure of the fuel nozzles,
2101M24G04, 2101M24G05, and DATES: This AD is effective December 6, which could lead to engine fire and
2101M24G06, at the next piece-part 2016. damage to the airplane.
exposure, with parts eligible for installation. The Director of the Federal Register Comments
(g) Definition approved the incorporation by reference
For the purpose of this AD, piece-part of a certain publication listed in this AD We gave the public the opportunity to
exposure is when the HPT stage 2 nozzle is as of December 6, 2016. participate in developing this AD. The
removed from the engine and completely ADDRESSES: For service information following presents the comments
disassembled. identified in this final rule, contact Pratt received on the NPRM and the FAA’s
& Whitney Division, 400 Main St., East response to each comment.
(h) Alternative Methods of Compliance
(AMOCs) Hartford, CT 06108; phone: 860–565– Request To Change Definition of Engine
The Manager, Engine Certification Office, 8770; fax: 860–565–4503. You may view Shop Visit
FAA, may approve AMOCs for this AD. Use this service information at the FAA,
Delta Air Lines (Delta) requested that
the procedures found in 14 CFR 39.19 to Engine & Propeller Directorate, 1200
the definition of an ‘‘engine shop visit’’
make your request. You may email your District Avenue, Burlington, MA. For
request to: ANE-AD-AMOC@faa.gov. be defined as the induction of an engine
information on the availability of this
into the shop for maintenance involving
(i) Related Information material at the FAA, call 781–238–7125.
the separation of pairs of major mating
It is also available on the internet at
For more information about this AD, engine flanges. Delta requested this
contact Martin Adler, Aerospace Engineer, http://www.regulations.gov by searching
change so that the definition of an
Engine & Propeller Directorate, FAA, 1200 for and locating Docket No. FAA–2016–
engine shop visit in this AD would be
District Avenue, Burlington, MA 01803; 5423.
consistent with prior ADs.
phone: 781–238–7157; fax: 781–238–7199;
Examining the AD Docket We disagree. The redefined shop visit
email: martin.adler@faa.gov.
You may examine the AD docket on interval as requested would result in
(j) Material Incorporated by Reference less frequent replacements of fuel
the Internet at http://
None. www.regulations.gov by searching for nozzles and an unacceptable fleet risk.
Issued in Burlington, Massachusetts, on and locating Docket No. FAA–2016– We did not change this AD.
October 25, 2016. 5423; or in person at the Docket Conclusion
Colleen M. D’Alessandro, Management Facility between 9 a.m.
We reviewed the relevant data,
Manager, Engine & Propeller Directorate, and 5 p.m., Monday through Friday,
considered the comment received, and
Aircraft Certification Service. except Federal holidays. The AD docket
determined that air safety and the
[FR Doc. 2016–26280 Filed 10–31–16; 8:45 am] contains this AD, the regulatory
public interest require adopting this AD
BILLING CODE 4910–13–P evaluation, any comments received, and
as proposed.
other information. The address for the
Docket Office (phone: 800–647–5527) is Related Service Information Under 1
DEPARTMENT OF TRANSPORTATION Document Management Facility, U.S. CFR Part 51
Department of Transportation, Docket We reviewed PW Alert Service
Federal Aviation Administration Operations, M–30, West Building Bulletin (ASB) PW4G–100–A73–45,
Ground Floor, Room W12–140, 1200 dated February 16, 2016. The ASB
14 CFR Part 39 New Jersey Avenue SE., Washington, describes procedures for inspecting and
[Docket No. FAA–2016–5423; Directorate
DC 20590. replacing the fuel nozzles. This service
Identifier 2016–NE–09–AD; Amendment 39– FOR FURTHER INFORMATION CONTACT: information is reasonably available
18694; AD 2016–22–05] Besian Luga, Aerospace Engineer, because the interested parties have
Engine Certification Office, FAA, Engine access to it through their normal course
RIN 2120–AA64 & Propeller Directorate, 1200 District of business or by the means identified
Avenue, Burlington, MA 01803; phone: in the ADDRESSES section.
Airworthiness Directives; Pratt &
781–238–7750; fax: 781–238–7199;
Whitney Division Turbofan Engines Costs of Compliance
email: besian.luga@faa.gov.
AGENCY: Federal Aviation SUPPLEMENTARY INFORMATION: We estimate that this AD will affect
Administration (FAA), DOT. 72 engines installed on airplanes of U.S.
Discussion
ACTION: Final rule. registry. We also estimate that it will
We issued a notice of proposed take about 2.2 hours per engine to
SUMMARY: We are adopting a new rulemaking (NPRM) to amend 14 CFR perform each inspection and 48 hours
airworthiness directive (AD) for certain part 39 by adding an AD that would per engine to replace the fuel nozzle.
Pratt & Whitney (PW) PW4164, apply to certain PW PW4164, PW4164– The average labor rate is $85 per hour.
PW4164–1D, PW4168, PW4168–1D, 1D, PW4168, PW4168–1D, PW4168A, We also estimate that parts cost would
PW4168A, PW4168A–1D, and PW4170 PW4168A–1D, and PW4170 turbofan be $15,780 per engine. Based on these
turbofan engines. This AD was engines. The NPRM published in the figures, we estimate the cost of this AD
prompted by several instances of fuel Federal Register on April 20, 2016 (81 on U.S. operators to be $1,443,384.
jstallworth on DSK7TPTVN1PROD with RULES
leaks on PW engines installed with the FR 23217) (‘‘the NPRM’’). The NPRM
Talon IIB combustion chamber was prompted by several instances of Authority for This Rulemaking
configuration. This AD requires initial fuel leaks on PW engines installed with Title 49 of the United States Code
and repetitive inspections of the the Talon IIB combustion chamber specifies the FAA’s authority to issue
affected fuel nozzles and their configuration. The NPRM proposed to rules on aviation safety. Subtitle I,
replacement with parts eligible for require initial and repetitive inspections section 106, describes the authority of
installation. We are issuing this AD to of the affected fuel nozzles and their the FAA Administrator. Subtitle VII:
VerDate Sep<11>2014 15:21 Oct 31, 2016 Jkt 241001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\01NOR1.SGM 01NOR1](https://thefederalregister.org/doc/81_FR_75895/page/3.svg)
Document Created: 2016-11-01 02:35:32
Document Modified: 2016-11-01 02:35:32
| 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; request for comments. | |
| Dates | This AD is effective November 16, 2016. | |
| Contact | Martin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7157; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 81 FR 75684 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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