81 FR 91880 - Airworthiness Directives; General Electric Company Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 243 (December 19, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 243 (December 19, 2016)
| Page Range | 91880-91882 | |
| FR Document | 2016-29679 |
[Federal Register Volume 81, Number 243 (Monday, December 19, 2016)] [Proposed Rules] [Pages 91880-91882] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-29679] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules [[Page 91880]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-7491; Directorate Identifier 2015-NE-39-AD] RIN 2120-AA64 Airworthiness Directives; General Electric Company Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede airworthiness directive (AD) 2016-13- 05, which applies to all General Electric Company (GE) GE90-76B, GE90- 77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines. AD 2016-13-05 requires eddy current inspection (ECI) of the high-pressure compressor (HPC) stage 8-10 spool at each shop visit for all affected engines and ECI or ultrasonic inspection (USI) for certain affected engines. Since we issued AD 2016-13-05, we determined that the risk of the failure of an HPC stage 8-10 spool was excessive without repetitive USI prior to shop visit. This proposed AD would require initial and repetitive on- wing USIs of the HPC stage 8-10 spool for certain engines prior to shop visit and ECI of all affected engines at each shop visit. We are proposing this AD to correct the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 2, 2017. 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513-552-3272; fax: 513-552-3329; 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- 7491; 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 proposed 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: John Frost, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781- 238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-7491; Directorate Identifier 2015-NE-39-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed 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 proposed AD. Discussion On June 15, 2016, we issued AD 2016-13-05, Amendment 39-18569 (81 FR 41208, June 24, 2016; corrected 81 FR 42475, June 30, 2016) (``AD 2016-13-05''), for GE GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90- 94B turbofan engines. AD 2016-13-05 requires an ECI or USI of the HPC stage 8-10 spool and removing from service those parts that fail inspection. AD 2016-13-05 resulted from an uncontained failure of the HPC stage 8-10 spool, leading to an airplane fire. We issued AD 2016- 13-05 to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane. Actions Since AD 2016-13-05 Was Issued We issued AD 2016-13-05 without including the repetitive USI prior to shop visit to expedite introduction of the corrective actions to the fleet. Since we issued AD 2016-13-05, we determined that a repetitive USI is required based on analysis that the risk of the failure of an HPC stage 8-10 spool is excessive without this inspection. Related Service Information We reviewed GE GE90 Service Bulletin (SB) SB 72-1151 R00, dated June 10, 2016. This SB describes procedures for an on-wing USI of the stage 8 web of the stage 8-10 spool. We also reviewed Chapter 72-31-08, Special Procedures 003; and Chapter 72-00-31, Special Procedures 006, in the GE GE90 Engine Manual, GEK100700, Revision 68, dated September 1, 2016. These procedures describe how to perform ECI of the stage 8 aft web of the stage 8-10 spool. FAA's Determination We are proposing 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. [[Page 91881]] Proposed AD Requirements This proposed AD would retain all the requirements of AD 2016-13- 05. This proposed AD would also require repetitive USI of the HPC 8-10 spool. Interim Action We consider this proposed AD interim action. GE is determining the root cause for the unsafe condition identified in this proposed AD. Once a root cause is identified, we will consider additional rulemaking. Costs of Compliance We estimate that this proposed AD affects 54 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection................. 7 work-hours x $85 $0 $595 per inspection $32,130 per per hour = $595 per cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. We have no way of determining the number of engines that might need this replacement: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Replacement of spool.......................... 0 work-hours x $85 per hour = $0 $780,000 $780,000 ---------------------------------------------------------------------------------------------------------------- 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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) 2016-13-05, Amendment 39-18569 (81 FR 41208, June 24, 2016; corrected 81 FR 42475, June 30, 2016), and adding the following new AD: General Electric Company: Docket No. FAA-2015-7491; Directorate Identifier 2015-NE-39-AD. (a) Comments Due Date The FAA must receive comments on this AD action by February 2, 2017. (b) Affected ADs This AD replaces AD 2016-13-05, Amendment 39-18569 (81 FR 41208, June 24, 2016; corrected 81 FR 42475, June 30, 2016). (c) Applicability This AD applies to General Electric Company (GE) GE90-76B, GE90- 77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with a high- pressure compressor (HPC) stage 8-10 spool, part numbers (P/Ns) 1694M80G04, 1844M90G01, or 1844M90G02, installed. (d) Subject Air Transport Association (ATA) of America Code 72, Engine General. (e) Unsafe Condition This AD was prompted by an uncontained failure of the HPC stage 8-10 spool. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For HPC stage 8-10 spool, P/N 1694M80G04, all serial numbers (S/Ns), or HPC stage 8-10 spool, P/N 1844M90G01 or 1844M90G02, with a S/N listed in Figure 1 to paragraph (f) of this AD; perform an on- wing ultrasonic inspection (USI) of the stage 8 aft web upper face as follows: (i) Perform an initial USI after reaching 8,000 cycles since new (CSN), but, before exceeding 9,000 CSN, or within 500 cycles in [[Page 91882]] service after July 29, 2016, whichever occurs later. (ii) Thereafter, perform a USI of the stage 8 aft web upper face every 500 cycles since last inspection. (iii) Compliance with paragraph (f)(2)(i) of this AD is terminating action for the initial and repetitive USIs specified by paragraphs (f)(1)(i) and (f)(1)(ii) of this AD. Figure 1 to Paragraph (f)--HPC Stage 8-10 Spool S/Ns -------------------------------------------------------------------------------------------------------------------------------------------------------- -------------------------------------------------------------------------------------------------------------------------------------------------------- Part Nos. Serial Nos. ----------------------------------------------------------------------------------------------------------------------- 1844M90G01...................... GWN005MF GWNBK753 GWNBS077 GWNBS497 GWNBS724 GWN005MG GWNBK754 GWNBS078 GWNBS499 GWNBS794 GWN0087M GWNBK841 GWNBS079 GWNBS500 GWNBS810 GWN0087N GWNBK842 GWNBS080 GWNBS501 GWNBS811 GWN00DGK GWNBK843 GWNBS081 GWNBS502 GWNBS812 GWN00DGL GWNBK844 GWNBS157 GWNBS609 GWNBS813 GWNBJ992 GWNBK952 GWNBS158 GWNBS610 GWNBS814 GWNBK667 GWNBK953 GWNBS159 GWNBS611 GWNBS910 GWNBK674 GWNBK954 GWNBS160 GWNBS612 GWNBS911 GWNBK675 GWNBK955 GWNBS266 GWNBS613 GWNBS912 GWNBK743 GWNBK956 GWNBS267 GWNBS614 GWNBS914 GWNBK744 GWNBK957 GWNBS268 GWNBS721 GWNBS915 GWNBK751 GWNBK958 GWNBS269 GWNBS722 GWNBS982 GWNBK752 GWNBK959 GWNBS270 GWNBS723 GWNBS983 1844M90G02...................... GWN00C2T GWN01C5N GWN02N8D GWN03RTM GWN04E21 GWN00C2V GWN01GE2 GWN02T3R GWN03RTP GWN04GHT GWN00G2N GWN01GE3 GWN02WGM GWN040RL GWN04GHW GWN00G2P GWN01GE4 GWN0311K GWN040RM GWN04GJ0 GWN00PFP GWN01GE6 GWN035PP GWN040RN GWN04JW6 GWN00PFR GWN01WH1 GWN038TD GWN040RP GWN04JW7 GWN00T2N GWN02688 GWN039TG GWN04202 GWN04JW8 GWN00YHV GWN02689 GWN03G2R GWN0435W GWN04L7K GWN0125G GWN0268A GWN03G2W GWN04360 GWN04L7L GWN0125H GWN02DP2 GWN03G30 GWN04361 GWN04MT7 GWN0166K GWN02DP3 GWN03JPC GWN04362 GWN04MT8 GWN01C5K GWN02F9F GWN03JPD GWN04ATG GWNBS984 GWN01C5L GWN02F9G GWN03N8P GWN04ATH ...................... GWN01C5M GWN02L9T GWN03N8R GWN04E20 ...................... -------------------------------------------------------------------------------------------------------------------------------------------------------- (2) For all HPC stage 8-10 spools, P/N 1694M80G04, 1844M90G01, or 1844M90G02, perform an eddy current inspection (ECI) of the stage 8 aft upper face as follows: (i) Perform an initial ECI of the stage 8 aft web upper face at the next shop visit after the effective date of this AD. (ii) Thereafter, perform an ECI of the stage 8 aft web upper face at each subsequent shop visit. (3) Remove from service any HPC stage 8-10 spool that fails the inspection required by paragraphs (f)(1) or (f)(2) of this AD, and replace with a spool eligible for installation. (g) Definition For the purpose of this AD, an engine shop visit is the induction of an engine into the shop for maintenance during which the compressor discharge pressure seal face is exposed. (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 (1) For more information about this AD, contact John Frost, Aerospace Engineer, Engine Certification Office, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238- 7199; email: [email protected]. (2) GE GE90 Service Bulletin (SB) SB 72-1151 R00, dated June 10, 2016, and Chapter 72-31-08, Special Procedures 003, and Chapter 72- 00-31, Special Procedures 006, in GE GE90 Engine Manual, GEK100700, Revision 68, dated September 1, 2016, can be obtained from GE using the contact information in paragraph (i)(3) of this AD. This SB describes procedures for an on-wing USI of the stage 8 web of the stage 8-10 spool. These engine manual procedures describe how to perform ECI of the stage 8 aft web of the stage 8-10 spool. (3) For service information identified in this proposed AD, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513-552-3272; fax: 513-552-3329; email: [email protected]. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (j) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on November 29, 2016. Colleen M. D'Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-29679 Filed 12-16-16; 8:45 am] BILLING CODE 4910-13-P
![91880
Proposed Rules Federal Register
Vol. 81, No. 243
Monday, December 19, 2016
This section of the FEDERAL REGISTER Room W12–140, 1200 New Jersey We will post all comments we
contains notices to the public of the proposed Avenue SE., Washington, DC 20590. receive, without change, to http://
issuance of rules and regulations. The • Hand Delivery: Deliver to Mail www.regulations.gov, including any
purpose of these notices is to give interested personal information you provide. We
address above between 9 a.m. and 5
persons an opportunity to participate in the will also post a report summarizing each
rule making prior to the adoption of the final p.m., Monday through Friday, except
rules. Federal holidays. substantive verbal contact we receive
For service information identified in about this proposed AD.
this NPRM, contact General Electric Discussion
DEPARTMENT OF TRANSPORTATION Company, GE-Aviation, Room 285, 1
Neumann Way, Cincinnati, OH 45215, On June 15, 2016, we issued AD
Federal Aviation Administration phone: 513–552–3272; fax: 513–552– 2016–13–05, Amendment 39–18569 (81
3329; email: geae.aoc@ge.com. You may FR 41208, June 24, 2016; corrected 81
14 CFR Part 39 view this service information at the FR 42475, June 30, 2016) (‘‘AD 2016–
FAA, Engine & Propeller Directorate, 13–05’’), for GE GE90–76B, GE90–77B,
[Docket No. FAA–2015–7491; Directorate
Identifier 2015–NE–39–AD] 1200 District Avenue, Burlington, MA. GE90–85B, GE90–90B, and GE90–94B
For information on the availability of turbofan engines. AD 2016–13–05
RIN 2120–AA64 this material at the FAA, call 781–238– requires an ECI or USI of the HPC stage
7125. 8–10 spool and removing from service
Airworthiness Directives; General those parts that fail inspection. AD
Electric Company Turbofan Engines Examining the AD Docket 2016–13–05 resulted from an
You may examine the AD docket on uncontained failure of the HPC stage 8–
AGENCY: Federal Aviation
the Internet at http:// 10 spool, leading to an airplane fire. We
Administration (FAA), DOT.
www.regulations.gov by searching for issued AD 2016–13–05 to prevent
ACTION: Notice of proposed rulemaking failure of the HPC stage 8–10 spool,
and locating Docket No. FAA–2015–
(NPRM). 7491; or in person at the Docket uncontained rotor release, damage to the
SUMMARY: We propose to supersede Management Facility between 9 a.m. engine, and damage to the airplane.
airworthiness directive (AD) 2016–13– and 5 p.m., Monday through Friday, Actions Since AD 2016–13–05 Was
05, which applies to all General Electric except Federal holidays. The AD docket Issued
Company (GE) GE90–76B, GE90–77B, contains this proposed AD, the
GE90–85B, GE90–90B, and GE90–94B regulatory evaluation, any comments We issued AD 2016–13–05 without
turbofan engines. AD 2016–13–05 received, and other information. The including the repetitive USI prior to
requires eddy current inspection (ECI) street address for the Docket Office shop visit to expedite introduction of
of the high-pressure compressor (HPC) (phone: 800–647–5527) is in the the corrective actions to the fleet. Since
stage 8–10 spool at each shop visit for ADDRESSES section. Comments will be we issued AD 2016–13–05, we
all affected engines and ECI or available in the AD docket shortly after determined that a repetitive USI is
ultrasonic inspection (USI) for certain receipt. required based on analysis that the risk
affected engines. Since we issued AD FOR FURTHER INFORMATION CONTACT: John of the failure of an HPC stage 8–10 spool
2016–13–05, we determined that the Frost, Aerospace Engineer, Engine is excessive without this inspection.
risk of the failure of an HPC stage 8–10 Certification Office, FAA, Engine & Related Service Information
spool was excessive without repetitive Propeller Directorate, 1200 District
USI prior to shop visit. This proposed Avenue, Burlington, MA 01803; phone: We reviewed GE GE90 Service
AD would require initial and repetitive 781–238–7756; fax: 781–238–7199; Bulletin (SB) SB 72–1151 R00, dated
on-wing USIs of the HPC stage 8–10 email: john.frost@faa.gov. June 10, 2016. This SB describes
spool for certain engines prior to shop SUPPLEMENTARY INFORMATION:
procedures for an on-wing USI of the
visit and ECI of all affected engines at stage 8 web of the stage 8–10 spool.
each shop visit. We are proposing this Comments Invited We also reviewed Chapter 72–31–08,
AD to correct the unsafe condition on We invite you to send any written Special Procedures 003; and Chapter
these products. relevant data, views, or arguments about 72–00–31, Special Procedures 006, in
DATES: We must receive comments on this proposed AD. Send your comments the GE GE90 Engine Manual,
this proposed AD by February 2, 2017. to an address listed under the GEK100700, Revision 68, dated
ADDRESSES: You may send comments, ADDRESSES section. Include ‘‘Docket No. September 1, 2016. These procedures
using the procedures found in 14 CFR FAA–2015–7491; Directorate Identifier describe how to perform ECI of the stage
11.43 and 11.45, by any of the following 2015–NE–39–AD’’ at the beginning of 8 aft web of the stage 8–10 spool.
sradovich on DSK3GMQ082PROD with PROPOSALS
methods: your comments. We specifically invite FAA’s Determination
• Federal eRulemaking Portal: Go to comments on the overall regulatory,
http://www.regulations.gov. Follow the economic, environmental, and energy We are proposing this AD because we
instructions for submitting comments. aspects of this proposed AD. We will evaluated all the relevant information
• Fax: 202–493–2251. consider all comments received by the and determined the unsafe condition
• Mail: U.S. Department of closing date and may amend this described previously is likely to exist or
Transportation, Docket Operations, proposed AD because of those develop in other products of the same
M–30, West Building Ground Floor, comments. type design.
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![Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules 91881
Proposed AD Requirements Interim Action Costs of Compliance
This proposed AD would retain all We consider this proposed AD We estimate that this proposed AD
the requirements of AD 2016–13–05. interim action. GE is determining the affects 54 engines installed on airplanes
root cause for the unsafe condition
This proposed AD would also require of U.S. registry.
identified in this proposed AD. Once a
repetitive USI of the HPC 8–10 spool. We estimate the following costs to
root cause is identified, we will
consider additional rulemaking. comply with this proposed AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspection ......... 7 work-hours × $85 per hour = $0 $595 per inspection cycle ............. $32,130 per inspection cycle.
$595 per inspection cycle.
We estimate the following costs to do be required based on the results of the determining the number of engines that
any necessary replacements that would proposed inspection. We have no way of might need this replacement:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Replacement of spool ................................................... 0 work-hours × $85 per hour = $0 ............................... $780,000 $780,000
Authority for This Rulemaking (2) Is not a ‘‘significant rule’’ under (a) Comments Due Date
the DOT Regulatory Policies and The FAA must receive comments on this
Title 49 of the United States Code
Procedures (44 FR 11034, February 26, AD action by February 2, 2017.
specifies the FAA’s authority to issue
1979),
rules on aviation safety. Subtitle I, (b) Affected ADs
(3) Will not affect intrastate aviation
Section 106, describes the authority of This AD replaces AD 2016–13–05,
in Alaska to the extent that it justifies
the FAA Administrator. Subtitle VII, Amendment 39–18569 (81 FR 41208, June
making a regulatory distinction, and
Aviation Programs, describes in more 24, 2016; corrected 81 FR 42475, June 30,
detail the scope of the Agency’s (4) Will not have a significant 2016).
authority. economic impact, positive or negative,
on a substantial number of small entities (c) Applicability
We are issuing this rulemaking under under the criteria of the Regulatory This AD applies to General Electric
the authority described in Subtitle VII, Flexibility Act. Company (GE) GE90–76B, GE90–77B, GE90–
Part A, Subpart III, Section 44701, 85B, GE90–90B, and GE90–94B turbofan
‘‘General requirements.’’ Under that List of Subjects in 14 CFR Part 39 engines with a high-pressure compressor
section, Congress charges the FAA with Air transportation, Aircraft, Aviation (HPC) stage 8–10 spool, part numbers (P/Ns)
promoting safe flight of civil aircraft in safety, Incorporation by reference, 1694M80G04, 1844M90G01, or 1844M90G02,
air commerce by prescribing regulations Safety.
installed.
for practices, methods, and procedures (d) Subject
the Administrator finds necessary for The Proposed Amendment
Air Transport Association (ATA) of
safety in air commerce. This regulation Accordingly, under the authority America Code 72, Engine General.
is within the scope of that authority delegated to me by the Administrator,
because it addresses an unsafe condition (e) Unsafe Condition
the FAA proposes to amend 14 CFR part
that is likely to exist or develop on 39 as follows: This AD was prompted by an uncontained
products identified in this rulemaking failure of the HPC stage 8–10 spool. We are
action. PART 39—AIRWORTHINESS issuing this AD to prevent failure of the HPC
DIRECTIVES stage 8–10 spool, uncontained rotor release,
Regulatory Findings damage to the engine, and damage to the
We have determined that this ■ 1. The authority citation for part 39 airplane.
proposed AD would not have federalism continues to read as follows: (f) Compliance
implications under Executive Order Authority: 49 U.S.C. 106(g), 40113, 44701. Comply with this AD within the
13132. This proposed AD would not compliance times specified, unless already
have a substantial direct effect on the § 39.13 [Amended] done.
States, on the relationship between the ■ 2. The FAA amends § 39.13 by (1) For HPC stage 8–10 spool, P/N
sradovich on DSK3GMQ082PROD with PROPOSALS
national Government and the States, or removing airworthiness directive (AD) 1694M80G04, all serial numbers (S/Ns), or
on the distribution of power and 2016–13–05, Amendment 39–18569 (81 HPC stage 8–10 spool, P/N 1844M90G01 or
responsibilities among the various FR 41208, June 24, 2016; corrected 81 1844M90G02, with a S/N listed in Figure 1
levels of government. to paragraph (f) of this AD; perform an on-
FR 42475, June 30, 2016), and adding
wing ultrasonic inspection (USI) of the stage
For the reasons discussed above, I the following new AD: 8 aft web upper face as follows:
certify that the proposed regulation: General Electric Company: Docket No. FAA– (i) Perform an initial USI after reaching
(1) Is not a ‘‘significant regulatory 2015–7491; Directorate Identifier 2015– 8,000 cycles since new (CSN), but, before
action’’ under Executive Order 12866, NE–39–AD. exceeding 9,000 CSN, or within 500 cycles in
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service after July 29, 2016, whichever occurs (ii) Thereafter, perform a USI of the stage (iii) Compliance with paragraph (f)(2)(i) of
later. 8 aft web upper face every 500 cycles since this AD is terminating action for the initial
last inspection. and repetitive USIs specified by paragraphs
(f)(1)(i) and (f)(1)(ii) of this AD.
FIGURE 1 TO PARAGRAPH (f)—HPC STAGE 8–10 SPOOL S/NS
Part Nos. Serial Nos.
1844M90G01 ...................................................................... GWN005MF GWNBK753 GWNBS077 GWNBS497 GWNBS724
GWN005MG GWNBK754 GWNBS078 GWNBS499 GWNBS794
GWN0087M GWNBK841 GWNBS079 GWNBS500 GWNBS810
GWN0087N GWNBK842 GWNBS080 GWNBS501 GWNBS811
GWN00DGK GWNBK843 GWNBS081 GWNBS502 GWNBS812
GWN00DGL GWNBK844 GWNBS157 GWNBS609 GWNBS813
GWNBJ992 GWNBK952 GWNBS158 GWNBS610 GWNBS814
GWNBK667 GWNBK953 GWNBS159 GWNBS611 GWNBS910
GWNBK674 GWNBK954 GWNBS160 GWNBS612 GWNBS911
GWNBK675 GWNBK955 GWNBS266 GWNBS613 GWNBS912
GWNBK743 GWNBK956 GWNBS267 GWNBS614 GWNBS914
GWNBK744 GWNBK957 GWNBS268 GWNBS721 GWNBS915
GWNBK751 GWNBK958 GWNBS269 GWNBS722 GWNBS982
GWNBK752 GWNBK959 GWNBS270 GWNBS723 GWNBS983
1844M90G02 ...................................................................... GWN00C2T GWN01C5N GWN02N8D GWN03RTM GWN04E21
GWN00C2V GWN01GE2 GWN02T3R GWN03RTP GWN04GHT
GWN00G2N GWN01GE3 GWN02WGM GWN040RL GWN04GHW
GWN00G2P GWN01GE4 GWN0311K GWN040RM GWN04GJ0
GWN00PFP GWN01GE6 GWN035PP GWN040RN GWN04JW6
GWN00PFR GWN01WH1 GWN038TD GWN040RP GWN04JW7
GWN00T2N GWN02688 GWN039TG GWN04202 GWN04JW8
GWN00YHV GWN02689 GWN03G2R GWN0435W GWN04L7K
GWN0125G GWN0268A GWN03G2W GWN04360 GWN04L7L
GWN0125H GWN02DP2 GWN03G30 GWN04361 GWN04MT7
GWN0166K GWN02DP3 GWN03JPC GWN04362 GWN04MT8
GWN01C5K GWN02F9F GWN03JPD GWN04ATG GWNBS984
GWN01C5L GWN02F9G GWN03N8P GWN04ATH
GWN01C5M GWN02L9T GWN03N8R GWN04E20
(2) For all HPC stage 8–10 spools, P/N (2) GE GE90 Service Bulletin (SB) SB 72– DEPARTMENT OF TRANSPORTATION
1694M80G04, 1844M90G01, or 1844M90G02, 1151 R00, dated June 10, 2016, and Chapter
perform an eddy current inspection (ECI) of 72–31–08, Special Procedures 003, and Federal Aviation Administration
the stage 8 aft upper face as follows: Chapter 72–00–31, Special Procedures 006,
(i) Perform an initial ECI of the stage 8 aft in GE GE90 Engine Manual, GEK100700,
web upper face at the next shop visit after the
14 CFR Part 39
Revision 68, dated September 1, 2016, can be
effective date of this AD. obtained from GE using the contact [Docket No. FAA–2016–9393; Directorate
(ii) Thereafter, perform an ECI of the stage information in paragraph (i)(3) of this AD. Identifier 2014–NM–199–AD]
8 aft web upper face at each subsequent shop This SB describes procedures for an on-wing
visit. RIN 2120–AA64
USI of the stage 8 web of the stage 8–10
(3) Remove from service any HPC stage 8–
10 spool that fails the inspection required by spool. These engine manual procedures
describe how to perform ECI of the stage 8 Airworthiness Directives; Airbus
paragraphs (f)(1) or (f)(2) of this AD, and
replace with a spool eligible for installation. aft web of the stage 8–10 spool. Airplanes
(3) For service information identified in
(g) Definition this proposed AD, contact General Electric
AGENCY: Federal Aviation
For the purpose of this AD, an engine shop Company, GE-Aviation, Room 285, 1 Administration (FAA), DOT.
visit is the induction of an engine into the Neumann Way, Cincinnati, OH 45215, ACTION: Notice of proposed rulemaking
shop for maintenance during which the phone: 513–552–3272; fax: 513–552–3329; (NPRM).
compressor discharge pressure seal face is email: geae.aoc@ge.com.
exposed. (4) You may view this service information SUMMARY: We propose to supersede
(h) Alternative Methods of Compliance at the FAA, Engine & Propeller Directorate, Airworthiness Directive (AD) 2013–13–
(AMOCs) 1200 District Avenue, Burlington, MA. For 16, which applies to all Airbus Model
information on the availability of this A330–200, A330–200 Freighter, A330–
The Manager, Engine Certification Office, material at the FAA, call 781–238–7125.
FAA, may approve AMOCs for this AD. Use 300 series airplanes, and all Airbus
the procedures found in 14 CFR 39.19 to (j) Material Incorporated by Reference Model A340–200, –300, –500, and –600
make your request. You may email your series airplanes. AD 2013–13–16
sradovich on DSK3GMQ082PROD with PROPOSALS
None.
request to: ANE-AD-AMOC@faa.gov. currently requires repetitive inspections
Issued in Burlington, Massachusetts, on for discrepancies of the ball-screw
(i) Related Information November 29, 2016. assembly of the trimmable horizontal
(1) For more information about this AD, Colleen M. D’Alessandro,
contact John Frost, Aerospace Engineer,
stabilizer actuator (THSA), repetitive
Manager, Engine & Propeller Directorate, greasing of the THSA ball-nut, and
Engine Certification Office, FAA, 1200
Aircraft Certification Service. replacement of the THSA if necessary;
District Avenue, Burlington, MA 01803;
phone: 781–238–7756; fax: 781–238–7199; [FR Doc. 2016–29679 Filed 12–16–16; 8:45 am] and modification or replacement (as
email: john.frost@faa.gov. BILLING CODE 4910–13–P applicable) of the ball-nut assembly,
VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\19DEP1.SGM 19DEP1](https://thefederalregister.org/doc/81_FR_92123/page/3.svg)
Document Created: 2016-12-17 03:15:29
Document Modified: 2016-12-17 03:15:29
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by February 2, 2017. | |
| Contact | John Frost, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781- 238-7199; email: [email protected] | |
| FR Citation | 81 FR 91880 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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