82 FR 21111 - Airworthiness Directives; General Electric Company Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 86 (May 5, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 86 (May 5, 2017)
| Page Range | 21111-21114 | |
| FR Document | 2017-09039 |
[Federal Register Volume 82, Number 86 (Friday, May 5, 2017)] [Rules and Regulations] [Pages 21111-21114] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-09039] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0165; Directorate Identifier 2015-NE-02-AD; Amendment 39-18868; AD 2017-09-06] RIN 2120-AA64 Airworthiness Directives; General Electric Company Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- [[Page 21112]] SUMMARY: We are superseding Airworthiness Directive (AD) 2015-15-03 for all General Electric Company (GE) GEnx turbofan engine models. AD 2015- 15-03 precluded the use of certain electronic engine control (EEC) full authority digital engine control (FADEC) software on GEnx turbofan engines. This AD requires removing a specific part and replacing it with a part eligible for installation and specifying the EEC FADEC software version for the affected GEnx turbofan engines. This AD was prompted by GE implementing final design changes that remove the unsafe condition. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective June 9, 2017. 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. 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- 0165; 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: Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781- 238-7120; fax: 781-238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2015-15-03, Amendment 39-18212 (80 FR 42707, July 20, 2015), (``AD 2015-15-03''). AD 2015-15-03 applied to all GE GEnx turbofan engine models. The NPRM published in the Federal Register on November 3, 2016 (81 FR 76540). The NPRM was prompted by GE implementing final design changes that remove the unsafe condition. The NPRM proposed to remove a specific part and replace it with a part eligible for installation and specify the EEC FADEC software version for the affected GEnx turbofan engines. We are issuing this AD to prevent engine failure, loss of thrust control, 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. Request To Change Compliance The Boeing Company and GE requested that we amend paragraph (f) to clarify which software versions are prohibited from being installed. They stated that the listed software versions do not contain the highest level of ice crystal icing (ICI) accommodation. We agree. We revised this AD because the listed software versions do not contain the highest level of ICI accommodation features. Also, the change requested makes the prohibition statement consistent with the AD removal requirements. Request To Add Terminating Action The Boeing Company requested that we add compliance to this AD as a terminating action to AD 2013-24-01, Amendment 39-17675 (78 FR 70851, November 27, 2013), (``AD 2013-24-01'') since it removes the unsafe condition. We partially agree. We agree that complying with this AD is terminating action for certain requirements of AD 2013-24-01. Therefore, we added a new terminating action paragraph (h) of this AD. Since complying with this AD is terminating action to certain requirements of AD 2013-24-01, we disagree that complying with this AD is terminating action for all requirements of AD 2013-24-01. Request To Add Terminating Action The Boeing Company requests that 747-8 and 747-8F aircraft with GEnx-2B engines that are operating with software, version C075, be granted a relaxation of the requirements in paragraphs (g) and (h) of AD 2013-24-01. They stated that an alternative method of compliance (AMOC) exists that grants a relaxation of the requirements of paragraphs (g) and (h) of AD 2013-24-01 as long as the aircraft engines have the required software versions. We disagree. Although Transport Airplane Directorate issued aircraft level AD 2013-24-01 and granted an AMOC, those are interim actions. Complying with this AD is required to remove the unsafe condition and is terminating action to certain requirements of AD 2013- 24-01. We did not change this AD. Request To Revise a Definition GE requested that we revise the definition of an engine shop visit. They suggested that we add ``Workscopes involving only externals, including transfer gearbox (TGB) and accessory gearbox (AGB) do not constitute an engine shop visit for the purpose of this AD.'' We disagree. The definition of a shop visit as ``the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine case flanges'' is a standard industry definition. Workscopes involving the TGB/AGB, or externals, do not separate major mating engine case flanges and do not constitute an engine shop visit for the purpose of this AD. We did not change this AD. Request To Change Compliance Time Cathay Pacific Airways Limited requested that we clarify which parts may be installed into the engine. We disagree. The FAA does not intend to specify which parts may be installed into the engine, only those parts that may not be installed into the engine. Specifying which parts are eligible for installation may inadvertently prohibit new parts that are introduced from being installed into the engine. We did not change this AD. Agreement With the Proposed AD The Air Line Pilots Association expressed agreement with 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 determined that the changes we made as the result of the comments we received:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic [[Page 21113]] burden on any operator or increase the scope of this AD. Related Service Information We reviewed GE GEnx-2B Service Bulletin (SB) 72-0241 R00, dated March 16, 2016 that describes removal and installation procedures of fan hub stator assembly booster outlet guide vane; GE GEnx-2B SB 73- 0041 R00, dated July 2, 2015 that describes reprogramming procedures for EEC FADEC software, version C075; and GE GEnx-1B SB 73-0044 R00, dated July 1, 2015 that describes reprograming procedures for EEC FADEC software, version B185. Costs of Compliance We estimate that this AD affects 130 engines installed on airplanes of U.S. registry. We estimate that it would take about 1 hour per engine to comply with the software installation required by this AD. We also estimate that 32 engines would require hardware replacement, which would take about 60 hours per engine. Required parts cost about $390,000 per engine. 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 $12,654,250. 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 We have determined that 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, 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 removing Airworthiness Directive (AD) 2015-15-03, Amendment 39-18212 (80 FR 42707, July 20, 2015), and adding the following new AD: 2017-09-06: General Electric Company: Amendment 39-18868; Docket No. FAA-2015-0165; Directorate Identifier 2015-NE-02-AD. (a) Effective Date This AD is effective June 9, 2017. (b) Affected ADs This AD replaces AD 2015-15-03, Amendment 39-18212 (80 FR 42707, July 20, 2015). This AD also affects AD 2013-24-01, Amendment 39- 17675 (78 FR 70851, November 27, 2013). (c) Applicability This AD applies to all General Electric Company (GE) GEnx-1B and GEnx-2B turbofan engines. (d) Unsafe Condition This AD was prompted by GE implementing final design changes that remove the unsafe condition. We are issuing this AD to prevent engine failure, loss of thrust control, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Thirty days after the effective date of this AD, do not operate any GE GEnx-1B engine with electronic engine control (EEC) full authority digital engine control (FADEC) software, version B180 or earlier, installed. (2) Thirty days after the effective date of this AD, do not operate any GE GEnx-2B engine with EEC FADEC software, version C068 or earlier, installed. (3) At the next shop visit after the effective date of this AD, remove from service all GE GEnx-2B67, -2B67B, and -2B67/P fan hub stator assembly booster outlet guide vanes, part number B1316-00720, and replace with a part eligible for installation. (f) Installation Prohibition After removing any software, version B180 or earlier, for the GE GEnx-1B engines; or software, version C068 or earlier, for the GE GEnx-2B engines, do not operate those engines with any software, version B180 or C068, or earlier. (g) Definition For the purpose of this AD, an ``engine shop visit'' is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine case flanges, except for the following situations which do not constitute an engine shop visit: (1) Separation of engine flanges solely for the purposes of transportation without subsequent maintenance does not constitute an engine shop visit. (2) Separation of engine flanges solely for the purpose of replacing the fan or propulsor without subsequent maintenance does not constitute an engine shop visit. (h) Terminating Action Compliance with this AD, for all engines installed on a specific airplane, is a terminating action to AD 2013-24-01 for that specific airplane, since it removes the unsafe condition on that specific airplane. (1) For GEnx-1B engines: (i) Compliance with paragraphs (e)(1) and (f) of this AD, for all engines on an airplane, is an approved terminating action for that airplane for paragraphs (g) and (i) of AD 2013-24-01. (ii) Note that paragraph (j) of AD 2013-24-01, which contains post-event inspection requirements, remains in force. (2) For GEnx-2B engines: (i) Compliance with paragraphs (e)(2), (e)(3), and (f) of this AD, for all engines on an airplane, is an approved terminating action for that airplane for paragraphs (g) and (h) of AD 2013-24- 01. (ii) Note that paragraph (j) of AD 2013-24-01, which contains post-event inspection requirements, remains in force. (i) 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]. (j) Related Information (1) For more information about this AD, contact Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7120; fax: 781-238-7199; email: [email protected]. [[Page 21114]] (2) GE GEnx-2B Service Bulletin (SB) 72-0241 R00, dated March 16, 2016; GE GEnx-2B SB 73-0041 R00, dated July 2, 2015; and GE GEnx-1B SB 73-0044 R00, dated July 1, 2015 can be obtained from GE, using the contact information in paragraph (j)(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]. Issued in Burlington, Massachusetts, on April 27, 2017. Robert J. Ganley, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2017-09039 Filed 5-4-17; 8:45 am] BILLING CODE 4910-13-P
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Special conditions are initially included in § 25.1445 when the special conditions upon publication in
applicable to the model for which they regulations were codified. the Federal Register.
are issued. Should the applicant apply The regulation is intended to protect The FAA is requesting comments to
for a supplemental type certificate to the flightcrew by ensuring that an allow interested persons to submit
modify any other model included on the adequate supply of oxygen is available views that may not have been submitted
same type certificate to incorporate the to complete a descent and land in response to the prior opportunities
same novel or unusual design feature, following a loss of cabin pressure. When for comment described above.
these special conditions would also the regulation was written, the only
passenger-oxygen system designs were List of Subjects in 14 CFR Part 25
apply to the other model under § 21.101.
In addition to the applicable supplemental-oxygen systems intended Aircraft, Aviation safety, Reporting
airworthiness regulations and special to protect passengers from hypoxia in and recordkeeping requirements.
conditions, the Boeing Model 737–700 the event of cabin decompression. The authority citation for these
airplane must comply with the fuel-vent Present designs of passenger-oxygen special conditions is as follows:
and exhaust-emission requirements of systems do not include design features
Authority: 49 U.S.C. 106(g), 40113, 44701,
14 CFR part 34 and the noise- that allow the crew to offer oxygen to
44702, 44704.
certification requirements of 14 CFR passengers during flight.
part 36. Furthermore, the potential hazard that The Special Conditions
The FAA issues special conditions, as can exist when the oxygen content of an Accordingly, pursuant to the
defined in 14 CFR 11.19, in accordance enclosed area becomes too high because authority delegated to me by the
with § 11.38, and they become part of of system leaks, malfunction, or damage Administrator, the following special
the type certification basis under from external sources, make it necessary conditions are issued as part of the type
§ 21.101. to ensure that adequate safety standards certification basis for Boeing Model
are applied to the design and 737–700 airplanes as modified by
Novel or Unusual Design Features installation of the oxygen system. These AMAC Aerospace Switzerland AG.
The Boeing Model 737–700 airplane, potential hazards also necessitate The distribution system for the
as changed, will incorporate the development and application of therapeutic-oxygen system must be
following novel or unusual design appropriate additional design and designed and installed to meet
features: installation standards. requirements similar to § 25.1445(a) as
These special conditions contain the
The installation of a supplemental follows:
additional safety standards that the
therapeutic oxygen system, for medical When oxygen is supplied to
Administrator considers necessary to
use, in a private, not-for-hire, not-for- passengers for both supplemental and
establish a level of safety equivalent to
common-carriage airplane. therapeutic purposes, the distribution
that established by the existing
Discussion system must be designed for either—
airworthiness standards.
1. A source of supplemental supply
AMAC has applied to modify a Applicability for protection from hypoxia following a
private business jet, a Boeing 737–700 As discussed above, these special loss of cabin pressure, and a separate
airplane, to include an oxygen supply conditions are applicable to the Boeing source for therapeutic purposes, or
for a dedicated medical-oxygen system. Model 737–700 airplane. Should AMAC 2. A common source of supply, with
The gaseous passenger-oxygen system apply at a later date for a supplemental means to separately reserve the
will be modified to include additional type certificate to modify any other minimum supply required by the
supply cylinders and several model included on Type Certificate no. passengers for supplemental use
therapeutic oxygen outlets located A16WE to incorporate the same novel or following a loss of cabin pressure.
throughout the airplane cabin. Each unusual design feature, these special Issued in Renton, Washington, on April 27,
therapeutic outlet will provide a conditions would apply to that model as 2017.
constant flow of oxygen at either 2 or 4 well. Paul Bernado,
liters per minute.
Conclusion Acting Manager, Transport Airplane
The flightcrew controls the flow of Directorate, Aircraft Certification Service.
therapeutic oxygen at all times during This action affects only certain novel [FR Doc. 2017–09173 Filed 5–4–17; 8:45 am]
flight. Therapeutic oxygen systems have or unusual design features on one model BILLING CODE 4910–13–P
been previously certified and were of airplane. It is not a rule of general
generally considered an extension of the applicability and affects only the
passenger-oxygen system for the applicant who applied to the FAA for DEPARTMENT OF TRANSPORTATION
purpose of defining the applicable approval of this feature on the airplane.
regulations. As a result, the applicable The substance of these special Federal Aviation Administration
regulations included those that applied conditions has been subject to the notice
to oxygen systems in general, or and comment period in several prior 14 CFR Part 39
supplemental oxygen systems. instances and has been derived without
Section 25.1445 includes standards substantive change from those [Docket No. FAA–2015–0165; Directorate
Identifier 2015–NE–02–AD; Amendment 39–
for oxygen-distribution systems when previously issued. It is unlikely that 18868; AD 2017–09–06]
oxygen is supplied to crew and prior public comment would result in a
passengers. If a common source of significant change from the substance RIN 2120–AA64
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supply is used, § 25.1445(a)(2) requires contained herein. Therefore, because a
a means to separately reserve the delay would significantly affect the Airworthiness Directives; General
minimum supply required for the certification of the airplane, which is Electric Company Turbofan Engines
flightcrew. This requirement was imminent, the FAA has determined that AGENCY: Federal Aviation
originally added to Civil Air Regulation prior public notice and comment are Administration (FAA), DOT.
(CAR) 4b.831 at amendment 4b–13, unnecessary and impracticable, and
ACTION: Final rule.
effective September 21, 1949, and was good cause exists for adopting these
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burden on any operator or increase the (1) Is not a ‘‘significant regulatory (2) Thirty days after the effective date of
scope of this AD. action’’ under Executive Order 12866, this AD, do not operate any GE GEnx–2B
(2) Is not a ‘‘significant rule’’ under engine with EEC FADEC software, version
Related Service Information DOT Regulatory Policies and Procedures C068 or earlier, installed.
We reviewed GE GEnx–2B Service (3) At the next shop visit after the effective
(44 FR 11034, February 26, 1979), date of this AD, remove from service all GE
Bulletin (SB) 72–0241 R00, dated March (3) Will not affect intrastate aviation GEnx–2B67, –2B67B, and –2B67/P fan hub
16, 2016 that describes removal and in Alaska, and stator assembly booster outlet guide vanes,
installation procedures of fan hub stator (4) Will not have a significant part number B1316–00720, and replace with
assembly booster outlet guide vane; GE economic impact, positive or negative, a part eligible for installation.
GEnx–2B SB 73–0041 R00, dated July 2, on a substantial number of small entities
(f) Installation Prohibition
2015 that describes reprogramming under the criteria of the Regulatory
procedures for EEC FADEC software, Flexibility Act. After removing any software, version B180
or earlier, for the GE GEnx–1B engines; or
version C075; and GE GEnx–1B SB 73– List of Subjects in 14 CFR Part 39 software, version C068 or earlier, for the GE
0044 R00, dated July 1, 2015 that GEnx–2B engines, do not operate those
describes reprograming procedures for Air transportation, Aircraft, Aviation
engines with any software, version B180 or
EEC FADEC software, version B185. safety, Incorporation by reference, C068, or earlier.
Safety.
Costs of Compliance (g) Definition
Adoption of the Amendment
We estimate that this AD affects 130 For the purpose of this AD, an ‘‘engine
engines installed on airplanes of U.S. Accordingly, under the authority shop visit’’ is the induction of an engine into
registry. We estimate that it would take delegated to me by the Administrator, the shop for maintenance involving the
the FAA amends 14 CFR part 39 as separation of pairs of major mating engine
about 1 hour per engine to comply with case flanges, except for the following
the software installation required by this follows:
situations which do not constitute an engine
AD. We also estimate that 32 engines shop visit:
PART 39—AIRWORTHINESS
would require hardware replacement, (1) Separation of engine flanges solely for
DIRECTIVES
which would take about 60 hours per the purposes of transportation without
engine. Required parts cost about ■ 1. The authority citation for part 39 subsequent maintenance does not constitute
$390,000 per engine. The average labor an engine shop visit.
continues to read as follows: (2) Separation of engine flanges solely for
rate is $85 per hour. Based on these
Authority: 49 U.S.C. 106(g), 40113, 44701. the purpose of replacing the fan or propulsor
figures, we estimate the cost of this AD without subsequent maintenance does not
on U.S. operators to be $12,654,250. § 39.13 [Amended] constitute an engine shop visit.
Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by (h) Terminating Action
Title 49 of the United States Code removing Airworthiness Directive (AD) Compliance with this AD, for all engines
specifies the FAA’s authority to issue 2015–15–03, Amendment 39–18212 (80 installed on a specific airplane, is a
rules on aviation safety. Subtitle I, FR 42707, July 20, 2015), and adding the terminating action to AD 2013–24–01 for that
Section 106, describes the authority of following new AD: specific airplane, since it removes the unsafe
the FAA Administrator. Subtitle VII, 2017–09–06: General Electric Company: condition on that specific airplane.
Amendment 39–18868; Docket No. (1) For GEnx–1B engines:
Aviation Programs, describes in more (i) Compliance with paragraphs (e)(1) and
detail the scope of the Agency’s FAA–2015–0165; Directorate Identifier
2015–NE–02–AD. (f) of this AD, for all engines on an airplane,
authority. is an approved terminating action for that
We are issuing this rulemaking under (a) Effective Date airplane for paragraphs (g) and (i) of AD
the authority described in Subtitle VII, This AD is effective June 9, 2017. 2013–24–01.
Part A, Subpart III, Section 44701, (ii) Note that paragraph (j) of AD 2013–24–
(b) Affected ADs 01, which contains post-event inspection
‘‘General requirements.’’ Under that
section, Congress charges the FAA with This AD replaces AD 2015–15–03, requirements, remains in force.
Amendment 39–18212 (80 FR 42707, July 20, (2) For GEnx–2B engines:
promoting safe flight of civil aircraft in
2015). This AD also affects AD 2013–24–01, (i) Compliance with paragraphs (e)(2),
air commerce by prescribing regulations (e)(3), and (f) of this AD, for all engines on
Amendment 39–17675 (78 FR 70851,
for practices, methods, and procedures November 27, 2013). an airplane, is an approved terminating
the Administrator finds necessary for action for that airplane for paragraphs (g) and
safety in air commerce. This regulation (c) Applicability (h) of AD 2013–24–01.
is within the scope of that authority This AD applies to all General Electric (ii) Note that paragraph (j) of AD 2013–24–
because it addresses an unsafe condition Company (GE) GEnx–1B and GEnx–2B 01, which contains post-event inspection
that is likely to exist or develop on turbofan engines. requirements, remains in force.
products identified in this rulemaking (d) Unsafe Condition (i) Alternative Methods of Compliance
action. This AD was prompted by GE (AMOCs)
Regulatory Findings implementing final design changes that The Manager, Engine Certification Office,
remove the unsafe condition. We are issuing FAA, may approve AMOCs for this AD. Use
We have determined that this AD will this AD to prevent engine failure, loss of the procedures found in 14 CFR 39.19 to
not have federalism implications under thrust control, and damage to the airplane. make your request. You may email your
Executive Order 13132. This AD will request to: ANE-AD-AMOC@faa.gov.
(e) Compliance
not have a substantial direct effect on (j) Related Information
jstallworth on DSK7TPTVN1PROD with RULES
the States, on the relationship between Comply with this AD within the
compliance times specified, unless already (1) For more information about this AD,
the national government and the States, done. contact Christopher McGuire, Aerospace
or on the distribution of power and (1) Thirty days after the effective date of Engineer, Engine Certification Office, FAA,
responsibilities among the various this AD, do not operate any GE GEnx–1B Engine & Propeller Directorate, 1200 District
levels of government. engine with electronic engine control (EEC) Avenue, Burlington, MA 01803; phone: 781–
For the reasons discussed above, I full authority digital engine control (FADEC) 238–7120; fax: 781–238–7199; email:
certify that this AD: software, version B180 or earlier, installed. chris.mcguire@faa.gov.
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(2) GE GEnx–2B Service Bulletin (SB) 72– For Examination incorporation by reference are realized
0241 R00, dated March 16, 2016; GE GEnx– and publication of the complete
2B SB 73–0041 R00, dated July 2, 2015; and 1. U.S. Department of Transportation,
Docket Ops–M30, 1200 New Jersey description of each SIAP, Takeoff
GE GEnx–1B SB 73–0044 R00, dated July 1, Minimums and ODP listed on FAA form
2015 can be obtained from GE, using the Avenue SE., West Bldg., Ground Floor,
contact information in paragraph (j)(3) of this Washington, DC 20590–0001. documents is unnecessary. This
AD. 2. The FAA Air Traffic Organization amendment provides the affected CFR
(3) For service information identified in Service Area in which the affected sections and specifies the types of
this AD, contact General Electric Company, airport is located; SIAPs, Takeoff Minimums and ODPs
GE Aviation, Room 285, 1 Neumann Way, 3. The office of Aeronautical with their applicable effective dates.
Cincinnati, OH 45215; phone: 513–552–3272; Navigation Products, 6500 South This amendment also identifies the
email: geae.aoc@ge.com. MacArthur Blvd., Oklahoma City, OK airport and its location, the procedure,
Issued in Burlington, Massachusetts, on 73169 or, and the amendment number.
April 27, 2017. 4. The National Archives and Records Availability and Summary of Material
Robert J. Ganley, Administration (NARA). For Incorporated by Reference
Acting Manager, Engine & Propeller information on the availability of this
Directorate, Aircraft Certification Service. material at NARA, call 202–741–6030, The material incorporated by
or go to: http://www.archives.gov/ reference is publicly available as listed
[FR Doc. 2017–09039 Filed 5–4–17; 8:45 am]
federal_register/code_of_federal_ in the ADDRESSES section.
BILLING CODE 4910–13–P
The material incorporated by
regulations/ibr_locations.html.
reference describes SIAPS, Takeoff
Availability Minimums and/or ODPS as identified in
DEPARTMENT OF TRANSPORTATION
All SIAPs and Takeoff Minimums and the amendatory language for part 97 of
Federal Aviation Administration ODPs are available online free of charge. this final rule.
Visit the National Flight Data Center at The Rule
14 CFR Part 97 nfdc.faa.gov to register. Additionally,
This amendment to 14 CFR part 97 is
individual SIAP and Takeoff Minimums
effective upon publication of each
[Docket No. 31130; Amdt. No. 3743] and ODP copies may be obtained from
separate SIAP, Takeoff Minimums and
the FAA Air Traffic Organization
ODP as Amended in the transmittal.
Standard Instrument Approach Service Area in which the affected
Some SIAP and Takeoff Minimums and
Procedures, and Takeoff Minimums airport is located.
textual ODP amendments may have
and Obstacle Departure Procedures; FOR FURTHER INFORMATION CONTACT: been issued previously by the FAA in a
Miscellaneous Amendments Thomas J. Nichols, Flight Procedure Flight Data Center (FDC) Notice to
Standards Branch (AFS–420), Flight Airmen (NOTAM) as an emergency
AGENCY: Federal Aviation
Technologies and Programs Divisions, action of immediate flight safety relating
Administration (FAA), DOT.
Flight Standards Service, Federal directly to published aeronautical
ACTION: Final rule. Aviation Administration, Mike charts.
Monroney Aeronautical Center, 6500 The circumstances that created the
SUMMARY: This rule establishes, amends,
South MacArthur Blvd., Oklahoma City, need for some SIAP and Takeoff
suspends, or removes Standard
OK 73169 (Mail Address: P.O. Box Minimums and ODP amendments may
Instrument Approach Procedures
25082, Oklahoma City, OK 73125) require making them effective in less
(SIAPs) and associated Takeoff
Telephone: (405) 954–4164. than 30 days. For the remaining SIAPs
Minimums and Obstacle Departure
SUPPLEMENTARY INFORMATION: This rule and Takeoff Minimums and ODPs, an
Procedures (ODPs) for operations at
certain airports. These regulatory amends Title 14 of the Code of Federal effective date at least 30 days after
actions are needed because of the Regulations, Part 97 (14 CFR part 97), by publication is provided.
adoption of new or revised criteria, or establishing, amending, suspending, or Further, the SIAPs and Takeoff
because of changes occurring in the removes SIAPS, Takeoff Minimums Minimums and ODPs contained in this
National Airspace System, such as the and/or ODPS. The complete regulatory amendment are based on the criteria
commissioning of new navigational description of each SIAP and its contained in the U.S. Standard for
facilities, adding new obstacles, or associated Takeoff Minimums or ODP Terminal Instrument Procedures
changing air traffic requirements. These for an identified airport is listed on FAA (TERPS). In developing these SIAPs and
changes are designed to provide safe form documents which are incorporated Takeoff Minimums and ODPs, the
and efficient use of the navigable by reference in this amendment under 5 TERPS criteria were applied to the
airspace and to promote safe flight U.S.C. 552(a), 1 CFR part 51, and 14 conditions existing or anticipated at the
operations under instrument flight rules CFR part 97.20. The applicable FAA affected airports. Because of the close
at the affected airports. forms are FAA Forms 8260–3, 8260–4, and immediate relationship between
8260–5, 8260–15A, and 8260–15B when these SIAPs, Takeoff Minimums and
DATES: This rule is effective May 5, required by an entry on 8260–15A. ODPs, and safety in air commerce, I find
2017. The compliance date for each The large number of SIAPs, Takeoff that notice and public procedure under
SIAP, associated Takeoff Minimums, Minimums and ODPs, their complex 5 U.S.C. 553(b) are impracticable and
and ODP is specified in the amendatory nature, and the need for a special format contrary to the public interest and,
provisions. make publication in the Federal where applicable, under 5 U.S.C. 553(d),
jstallworth on DSK7TPTVN1PROD with RULES
The incorporation by reference of Register expensive and impractical. good cause exists for making some
certain publications listed in the Further, airmen do not use the SIAPs effective in less than 30 days.
regulations is approved by the Director regulatory text of the SIAPs, Takeoff The FAA has determined that this
of the Federal Registe as of May 5, 2017. Minimums or ODPs, but instead refer to regulation only involves an established
ADDRESSES: Availability of matters their graphic depiction on charts body of technical regulations for which
incorporated by reference in the printed by publishers of aeronautical frequent and routine amendments are
amendment is as follows: materials. Thus, the advantages of necessary to keep them operationally
VerDate Sep<11>2014 14:00 May 04, 2017 Jkt 241001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\05MYR1.SGM 05MYR1](https://thefederalregister.org/doc/82_FR_21197/page/4.svg)
Document Created: 2018-11-08 08:39:28
Document Modified: 2018-11-08 08:39:28
| 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 June 9, 2017. | |
| Contact | Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781- 238-7120; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 82 FR 21111 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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