81_FR_1298 81 FR 1291 - Airworthiness Directives; General Electric Company Turbofan Engines

81 FR 1291 - Airworthiness Directives; General Electric Company Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 7 (January 12, 2016)

Page Range1291-1292
FR Document2015-33075

We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, -77B, -85B, -90B, and -94B turbofan engines. This AD requires performing an eddy current inspection (ECI) or ultrasonic inspection (USI) of the high-pressure compressor (HPC) stage 8-10 spool and removing from service those parts that fail inspection. This AD was prompted by an uncontained failure of the HPC stage 8-10 spool, leading to an airplane fire. 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.

Federal Register, Volume 81 Issue 7 (Tuesday, January 12, 2016) 
[Federal Register Volume 81, Number 7 (Tuesday, January 12, 2016)]
[Rules and Regulations]
[Pages 1291-1292]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-33075]



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Federal Register / Vol. 81, No. 7 / Tuesday, January 12, 2016 / Rules 
and Regulations

[[Page 1291]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-6823; Directorate Identifier 2015-NE-38-AD; 
Amendment 39-18360; AD 2015-27-01]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
General Electric Company (GE) GE90-76B, -77B, -85B, -90B, and -94B 
turbofan engines. This AD requires performing an eddy current 
inspection (ECI) or ultrasonic inspection (USI) of the high-pressure 
compressor (HPC) stage 8-10 spool and removing from service those parts 
that fail inspection. This AD was prompted by an uncontained failure of 
the HPC stage 8-10 spool, leading to an airplane fire. 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.

DATES: This AD is effective January 27, 2016.
    We must receive comments on this AD by February 26, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
6823; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7756; fax: 
781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We received a report of an HPC stage 8-10 spool uncontained failure 
resulting in an airplane fire. Ongoing investigations have determined 
that a crack initiated in the stage 8 aft web upper face of the HPC 8-
10 spool and propagated until spool rupture. The root cause of the 
crack initiation is not yet known. This condition, if not corrected, 
could result in failure of the HPC stage 8-10 spool, uncontained rotor 
release, damage to the engine, and damage to the airplane. We are 
issuing this AD to correct the unsafe condition on these products.

Related Service Information

    We reviewed GE Service Bulletin (SB) No. GE90 S/B 72-1145, dated 
November 24, 2015. The SB describes procedures for one-time on-wing USI 
of the stage 8 web of the stage 8-10 spool. We also reviewed the 
following chapters of GE GE90 Engine Manual, GEK100700, Revision 66, 
dated September 1, 2015:
     Chapter 72-31-08, Special Procedure 003, piece-part level 
ECI,
     Chapter 72-00-31, Special Procedure 006, rotor assembly 
and module level ECI and,
     Chapter 72-00-31, Special Procedure 007, rotor assembly 
level USI.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires accomplishing an ECI or USI of the stage 8 aft web 
upper face of the HPC stage 8-10 spool and removing from service those 
parts that fail inspection.

Interim Action

    We consider this AD interim action. GE is determining the root 
cause for the unsafe condition identified in this AD. Once a root cause 
is identified, we might consider additional rulemaking.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule based on the 
reported engine failure. Therefore, we find that notice and opportunity 
for prior public comment are impracticable and that good cause exists 
for making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2015-6823; Directorate 
Identifier 2015-NE-38-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.

[[Page 1292]]

    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 1 engine installed on an airplane 
of U.S. registry. We also estimate that it will take about 7 hours per 
engine to comply with this AD. The average labor rate is $85 per hour. 
Required parts cost about $780,000 per engine. Based on these figures, 
we estimate the total cost of the AD to U.S. operators to be $780,595.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation Programs'' 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2015-27-01 General Electric Company: Amendment 39-18360; Docket No. 
FAA-2015-6823; Directorate Identifier 2015-NE-38-AD.

(a) Effective Date

    This AD is effective January 27, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) GE90-76B, -77B, 
-85B, -90B, and -94B turbofan engines with high-pressure compressor 
(HPC) stage 8-10 spool, part number 1694M80G04, installed.

(d) Unsafe Condition

    This AD was prompted by an uncontained failure of the HPC stage 
8-10 spool, leading to an airplane fire. 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.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Perform an eddy current inspection or ultrasonic inspection 
of the stage 8 aft web upper face of the HPC stage 8-10 spool for 
cracks as follows:
    (i) For HPC stage 8-10 spools with serial number (S/N) GWNHC086 
or GWNHB875, inspect within 150 cycles-in-service (CIS), after the 
effective date of this AD.
    (ii) For HPC stage 8-10 spools with S/N GWNHC154, GWNHA455, 
GWNHC153, or GWNHB516, inspect within 300 CIS, after the effective 
date of this AD.
    (2) Remove from service any HPC stage 8-10 spool that fails the 
inspection required by paragraph (e)(1) of this AD and replace the 
spool with a spool eligible for installation.

(f) 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].

(g) Related Information

    For more information about this AD, contact John Frost, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7756; fax: 781-238-7199; email: 
[email protected].

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on December 21, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-33075 Filed 1-11-16; 8:45 am]
BILLING CODE 4910-13-P

1291 Rules and Regulations Federal Register Vol. 81, No. 7 Tuesday, January 12, 2016 This section of the FEDERAL REGISTER W12–140, 1200 New Jersey Avenue SE., • Chapter 72–00–31, Special contains regulatory documents having general Washington, DC 20590. Procedure 006, rotor assembly and applicability and legal effect, most of which • Hand Delivery: U.S. Department of module level ECI and, are keyed to and codified in the Code of Transportation, Docket Operations, M– • Chapter 72–00–31, Special Federal Regulations, which is published under 30, West Building Ground Floor, Room 50 titles pursuant to 44 U.S.C. 1510. Procedure 007, rotor assembly level USI. W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. FAA’s Determination The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of and 5 p.m., Monday through Friday, We are issuing this AD because we new books are listed in the first FEDERAL except Federal holidays. evaluated all the relevant information REGISTER issue of each week. and determined the unsafe condition Examining the AD Docket described previously is likely to exist or You may examine the AD docket on develop in other products of the same DEPARTMENT OF TRANSPORTATION the Internet at http:// type design. www.regulations.gov by searching for Federal Aviation Administration and locating Docket No. FAA–2015– AD Requirements 6823; or in person at the Docket This AD requires accomplishing an 14 CFR Part 39 Management Facility between 9 a.m. ECI or USI of the stage 8 aft web upper and 5 p.m., Monday through Friday, [Docket No. FAA–2015–6823; Directorate face of the HPC stage 8–10 spool and Identifier 2015–NE–38–AD; Amendment 39– except Federal holidays. The AD docket removing from service those parts that 18360; AD 2015–27–01] contains this AD, the regulatory fail inspection. evaluation, any comments received, and RIN 2120–AA64 other information. The street address for Interim Action the Docket Office (phone: 800–647– Airworthiness Directives; General We consider this AD interim action. 5527) is in the ADDRESSES section. Electric Company Turbofan Engines GE is determining the root cause for the Comments will be available in the AD unsafe condition identified in this AD. AGENCY: Federal Aviation docket shortly after receipt. Once a root cause is identified, we Administration (FAA), DOT. FOR FURTHER INFORMATION CONTACT: John might consider additional rulemaking. ACTION: Final rule; request for Frost, Aerospace Engineer, Engine comments. Certification Office, FAA, Engine & FAA’s Justification and Determination Propeller Directorate, 12 New England of the Effective Date SUMMARY: We are adopting a new Executive Park, Burlington, MA 01803; An unsafe condition exists that airworthiness directive (AD) for all phone: 781–238–7756; fax: 781–238– requires the immediate adoption of this General Electric Company (GE) GE90– 7199; email: john.frost@faa.gov. AD. The FAA has found that the risk to 76B, –77B, –85B, –90B, and –94B SUPPLEMENTARY INFORMATION: the flying public justifies waiving notice turbofan engines. This AD requires and comment prior to adoption of this performing an eddy current inspection Discussion rule based on the reported engine (ECI) or ultrasonic inspection (USI) of We received a report of an HPC stage failure. Therefore, we find that notice the high-pressure compressor (HPC) 8–10 spool uncontained failure resulting and opportunity for prior public stage 8–10 spool and removing from in an airplane fire. Ongoing investigations have determined that a comment are impracticable and that service those parts that fail inspection. good cause exists for making this This AD was prompted by an crack initiated in the stage 8 aft web upper face of the HPC 8–10 spool and amendment effective in less than 30 uncontained failure of the HPC stage 8– days. 10 spool, leading to an airplane fire. We propagated until spool rupture. The root are issuing this AD to prevent failure of cause of the crack initiation is not yet Comments Invited the HPC stage 8–10 spool, uncontained known. This condition, if not corrected, could result in failure of the HPC stage This AD is a final rule that involves rotor release, damage to the engine, and requirements affecting flight safety and damage to the airplane. 8–10 spool, uncontained rotor release, damage to the engine, and damage to the was not preceded by notice and an DATES: This AD is effective January 27, opportunity for public comment. 2016. airplane. We are issuing this AD to correct the unsafe condition on these However, we invite you to send any We must receive comments on this written data, views, or arguments about AD by February 26, 2016. products. this AD. Send your comments to an ADDRESSES: You may send comments, Related Service Information address listed under the ADDRESSES using the procedures found in 14 CFR We reviewed GE Service Bulletin (SB) section. Include ‘‘Docket No. FAA– 11.43 and 11.45, by any of the following No. GE90 S/B 72–1145, dated November 2015–6823; Directorate Identifier 2015– methods: 24, 2015. The SB describes procedures NE–38–AD’’ at the beginning of your • Federal eRulemaking Portal: Go to for one-time on-wing USI of the stage 8 comments. We specifically invite tkelley on DSK3SPTVN1PROD with RULES http://www.regulations.gov. Follow the web of the stage 8–10 spool. We also comments on the overall regulatory, instructions for submitting comments. reviewed the following chapters of GE economic, environmental, and energy • Fax: 202–493–2251. GE90 Engine Manual, GEK100700, aspects of this AD. We will consider all • Mail: U.S. Department of Revision 66, dated September 1, 2015: comments received by the closing date Transportation, Docket Operations, M– • Chapter 72–31–08, Special and may amend this AD because of 30, West Building Ground Floor, Room Procedure 003, piece-part level ECI, those comments. VerDate Sep<11>2014 20:17 Jan 11, 2016 Jkt 238001 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\12JAR1.SGM 12JAR1

1292 Federal Register / Vol. 81, No. 7 / Tuesday, January 12, 2016 / Rules and Regulations We will post all comments we List of Subjects in 14 CFR Part 39 make your request. You may email your receive, without change, to http:// request to: ANE-AD-AMOC@faa.gov. Air transportation, Aircraft, Aviation www.regulations.gov, including any safety, Incorporation by reference, (g) Related Information personal information you provide. We Safety. For more information about this AD, will also post a report summarizing each contact John Frost, Aerospace Engineer, substantive verbal contact we receive Adoption of the Amendment Engine Certification Office, FAA, Engine & about this AD. Accordingly, under the authority Propeller Directorate, 12 New England delegated to me by the Administrator, Executive Park, Burlington, MA 01803; Costs of Compliance phone: 781–238–7756; fax: 781–238–7199; the FAA amends 14 CFR part 39 as We estimate that this AD affects 1 email: john.frost@faa.gov. follows: engine installed on an airplane of U.S. (h) Material Incorporated by Reference registry. We also estimate that it will PART 39—AIRWORTHINESS None. take about 7 hours per engine to comply DIRECTIVES with this AD. The average labor rate is Issued in Burlington, Massachusetts, on $85 per hour. Required parts cost about ■ 1. The authority citation for part 39 December 21, 2015. $780,000 per engine. Based on these continues to read as follows: Colleen M. D’Alessandro, figures, we estimate the total cost of the Authority: 49 U.S.C. 106(g), 40113, 44701. Directorate Manager, Engine & Propeller AD to U.S. operators to be $780,595. Directorate, Aircraft Certification Service. § 39.13 [Amended] [FR Doc. 2015–33075 Filed 1–11–16; 8:45 am] Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by adding BILLING CODE 4910–13–P Title 49 of the United States Code the following new airworthiness specifies the FAA’s authority to issue directive (AD): rules on aviation safety. Subtitle I, DEPARTMENT OF TRANSPORTATION 2015–27–01 General Electric Company: section 106, describes the authority of Amendment 39–18360; Docket No. the FAA Administrator. ‘‘Subtitle VII: Federal Aviation Administration FAA–2015–6823; Directorate Identifier Aviation Programs’’ describes in more 2015–NE–38–AD. detail the scope of the Agency’s 14 CFR Parts 61 and 183 (a) Effective Date authority. [Docket No.: FAA–2010–1127; Amdt. Nos. We are issuing this rulemaking under This AD is effective January 27, 2016. 61–135 and 183–15] the authority described in Subtitle VII, (b) Affected ADs RIN 2120–AJ42 Part A, Subpart III, Section 44701: None. ‘‘General requirements.’’ Under that Student Pilot Application section, Congress charges the FAA with (c) Applicability Requirements promoting safe flight of civil aircraft in This AD applies to General Electric air commerce by prescribing regulations Company (GE) GE90–76B, –77B, –85B, –90B, AGENCY: Federal Aviation for practices, methods, and procedures and –94B turbofan engines with high- Administration (FAA), DOT. pressure compressor (HPC) stage 8–10 spool, ACTION: Final rule. the Administrator finds necessary for part number 1694M80G04, installed. safety in air commerce. This regulation is within the scope of that authority (d) Unsafe Condition SUMMARY: This action requires because it addresses an unsafe condition applicants to apply for a student pilot This AD was prompted by an uncontained that is likely to exist or develop on failure of the HPC stage 8–10 spool, leading certificate through a Flight Standards products identified in this rulemaking to an airplane fire. We are issuing this AD to District Office, designated pilot action. prevent failure of the HPC stage 8–10 spool, examiner, airman certification uncontained rotor release, damage to the representative associated with a pilot Regulatory Findings engine, and damage to the airplane. school, or certified flight instructor. This AD will not have federalism (e) Compliance Aviation Medical Examiners will no implications under Executive Order longer issue a combination medical Comply with this AD within the 13132. This AD will not have a compliance times specified, unless already certificate and student pilot certificate. substantial direct effect on the States, on done. Student pilot certificates will be issued the relationship between the national (1) Perform an eddy current inspection or on the same medium as other pilot government and the States, or on the ultrasonic inspection of the stage 8 aft web certificates and will have no expiration distribution of power and upper face of the HPC stage 8–10 spool for date. All student pilot certificates issued responsibilities among the various cracks as follows: before the effective date of this final rule (i) For HPC stage 8–10 spools with serial will expire according to their terms levels of government. number (S/N) GWNHC086 or GWNHB875, For the reasons discussed above, I unless they are replaced by another inspect within 150 cycles-in-service (CIS), certify that this AD: pilot certificate. This final rule responds after the effective date of this AD. (1) Is not a ‘‘significant regulatory (ii) For HPC stage 8–10 spools with S/N to section 4012 of the Intelligence action’’ under Executive Order 12866, GWNHC154, GWNHA455, GWNHC153, or Reform and Terrorism Prevention Act (2) Is not a ‘‘significant rule’’ under GWNHB516, inspect within 300 CIS, after the and facilitates security vetting by the DOT Regulatory Policies and Procedures effective date of this AD. Transportation Security Administration (44 FR 11034, February 26, 1979), (2) Remove from service any HPC stage 8– of student pilot applicants prior to (3) Will not affect intrastate aviation 10 spool that fails the inspection required by certificate issuance. This action in Alaska to the extent that it justifies paragraph (e)(1) of this AD and replace the withdraws the proposal for pilot tkelley on DSK3SPTVN1PROD with RULES making a regulatory distinction, and spool with a spool eligible for installation. certificates to include a photograph of (4) Will not have a significant (f) Alternative Methods of Compliance the individual pilot. Section 321 of the economic impact, positive or negative, (AMOCs) FAA Modernization and Reform Act of on a substantial number of small entities The Manager, Engine Certification Office, 2012 supersedes section 4022 of the under the criteria of the Regulatory FAA, may approve AMOCs for this AD. Use Intelligence Reform and Terrorism Flexibility Act. the procedures found in 14 CFR 39.19 to Prevention Act, which provided the VerDate Sep<11>2014 20:17 Jan 11, 2016 Jkt 238001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\12JAR1.SGM 12JAR1


Document Created: 2016-01-12 01:23:02
Document Modified: 2016-01-12 01:23:02
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule; request for comments.
DatesThis AD is effective January 27, 2016.
ContactJohn Frost, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email: [email protected]
FR Citation81 FR 1291 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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