Airworthiness Directives; General Electric Company Turbofan Engines, 91880-91882 [2016-29679]

Download as PDF 91880 Proposed Rules Federal Register Vol. 81, No. 243 Monday, December 19, 2016 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. 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 Examining the AD Docket Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 https://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, sradovich on DSK3GMQ082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 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: geae.aoc@ge.com. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238– 7125. You may examine the AD docket on the Internet at https:// 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: john.frost@faa.gov. 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. PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 We will post all comments we receive, without change, to https:// 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. E:\FR\FM\19DEP1.SGM 19DEP1 91881 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules Proposed AD Requirements 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. 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. 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 Action Labor cost Parts cost Inspection ......... 7 work-hours × $85 per hour = $595 per inspection cycle. We estimate the following costs to do any necessary replacements that would Cost on U.S. operators Cost per product $0 $595 per inspection cycle ............. be required based on the results of the proposed inspection. We have no way of $32,130 per inspection cycle. determining the number of engines that might need this replacement: ON-CONDITION COSTS Action Labor cost Replacement of spool ................................................... 0 work-hours × $85 per hour = $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. sradovich on DSK3GMQ082PROD with PROPOSALS 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, VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 (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. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 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. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 $780,000 Cost per product $780,000 (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 The Proposed Amendment § 39.13 Parts cost 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 onwing 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 E:\FR\FM\19DEP1.SGM 19DEP1 91882 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules 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 ...................................................................... 1844M90G02 ...................................................................... (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. sradovich on DSK3GMQ082PROD with PROPOSALS (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: ANE-AD-AMOC@faa.gov. (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: john.frost@faa.gov. VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 GWN005MF GWN005MG GWN0087M GWN0087N GWN00DGK GWN00DGL GWNBJ992 GWNBK667 GWNBK674 GWNBK675 GWNBK743 GWNBK744 GWNBK751 GWNBK752 GWN00C2T GWN00C2V GWN00G2N GWN00G2P GWN00PFP GWN00PFR GWN00T2N GWN00YHV GWN0125G GWN0125H GWN0166K GWN01C5K GWN01C5L GWN01C5M GWNBK753 GWNBK754 GWNBK841 GWNBK842 GWNBK843 GWNBK844 GWNBK952 GWNBK953 GWNBK954 GWNBK955 GWNBK956 GWNBK957 GWNBK958 GWNBK959 GWN01C5N GWN01GE2 GWN01GE3 GWN01GE4 GWN01GE6 GWN01WH1 GWN02688 GWN02689 GWN0268A GWN02DP2 GWN02DP3 GWN02F9F GWN02F9G GWN02L9T GWNBS077 GWNBS078 GWNBS079 GWNBS080 GWNBS081 GWNBS157 GWNBS158 GWNBS159 GWNBS160 GWNBS266 GWNBS267 GWNBS268 GWNBS269 GWNBS270 GWN02N8D GWN02T3R GWN02WGM GWN0311K GWN035PP GWN038TD GWN039TG GWN03G2R GWN03G2W GWN03G30 GWN03JPC GWN03JPD GWN03N8P GWN03N8R (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: geae.aoc@ge.com. (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 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 GWNBS497 GWNBS499 GWNBS500 GWNBS501 GWNBS502 GWNBS609 GWNBS610 GWNBS611 GWNBS612 GWNBS613 GWNBS614 GWNBS721 GWNBS722 GWNBS723 GWN03RTM GWN03RTP GWN040RL GWN040RM GWN040RN GWN040RP GWN04202 GWN0435W GWN04360 GWN04361 GWN04362 GWN04ATG GWN04ATH GWN04E20 GWNBS724 GWNBS794 GWNBS810 GWNBS811 GWNBS812 GWNBS813 GWNBS814 GWNBS910 GWNBS911 GWNBS912 GWNBS914 GWNBS915 GWNBS982 GWNBS983 GWN04E21 GWN04GHT GWN04GHW GWN04GJ0 GWN04JW6 GWN04JW7 GWN04JW8 GWN04L7K GWN04L7L GWN04MT7 GWN04MT8 GWNBS984 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9393; Directorate Identifier 2014–NM–199–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2013–13– 16, which applies to all Airbus Model A330–200, A330–200 Freighter, A330– 300 series airplanes, and all Airbus Model A340–200, –300, –500, and –600 series airplanes. AD 2013–13–16 currently requires repetitive inspections for discrepancies of the ball-screw assembly of the trimmable horizontal stabilizer actuator (THSA), repetitive greasing of the THSA ball-nut, and replacement of the THSA if necessary; and modification or replacement (as applicable) of the ball-nut assembly, SUMMARY: E:\FR\FM\19DEP1.SGM 19DEP1

Agencies

[Federal Register Volume 81, Number 243 (Monday, December 19, 2016)]
[Proposed Rules]
[Pages 91880-91882]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[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 https://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: geae.aoc@ge.com. 
You may view this service information at the FAA, Engine & Propeller 
Directorate, 1200 District Avenue, Burlington, MA. For information on 
the availability of this material at the FAA, call 781-238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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: john.frost@faa.gov.

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 https://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: ANE-AD-AMOC@faa.gov.

 (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: john.frost@faa.gov.
    (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: geae.aoc@ge.com.
    (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