Document ID: FAA-2015-6823-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: General Electric Company Turbofan Engines
Posted Date: 2016-01-12T05:00Z

[Federal Register Volume 81, Number 7 (Tuesday, January 12, 2016)]
[Rules and Regulations]
[Pages 1291-1292]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[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: john.frost@faa.gov.

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: ANE-AD-AMOC@faa.gov.

(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: 
john.frost@faa.gov.

(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]
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