81 FR 19516 - Airworthiness Directives; International Aero Engines AG Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 65 (April 5, 2016)

We propose to adopt a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2525- D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan engines. This proposed AD was prompted by the fracture of the high-pressure turbine (HPT) stage 2 hub during flight, which resulted in an in-flight shutdown (IFSD), undercowl fire, and smoke in the cabin. This proposed AD would require inspecting the HPT stage 1 hub and HPT stage 2 hub, and, if necessary, their replacement with parts that are eligible for installation. We are proposing this AD to prevent failure of the HPT stage 1 or HPT stage 2 hubs, which could result in uncontained HPT blade release, damage to the engine, and damage to the airplane.

[Federal Register Volume 81, Number 65 (Tuesday, April 5, 2016)]
[Proposed Rules]
[Pages 19516-19518]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-07579]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-4123; Directorate Identifier 2016-NE-06-AD]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines AG Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2525-
D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 
turbofan engines. This proposed AD was prompted by the fracture of the 
high-pressure turbine (HPT) stage 2 hub during flight, which resulted 
in an in-flight shutdown (IFSD), undercowl fire, and smoke in the 
cabin. This proposed AD would require inspecting the HPT stage 1 hub 
and HPT stage 2 hub, and, if necessary, their replacement with parts 
that are eligible for installation. We are proposing this AD to prevent 
failure of the HPT stage 1 or HPT stage 2 hubs, which could result in 
uncontained HPT blade release, damage to the engine, and damage to the 
airplane.

DATES: We must receive comments on this proposed AD by June 6, 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: 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 
International Aero Engines AG, 400 Main Street, East Hartford, CT 
06118; phone: 860-368-3700; fax: 860-368-4600; email: 
[email protected]; Internet: https://www.iaeworld.com. You may view 
this service information at the FAA, Engine & Propeller Directorate, 
1200 District Avenue, Burlington, MA. For

[[Page 19517]]

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-2016-
4123 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: Brian Kierstead, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7772; 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 proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2016-4123; 
Directorate Identifier 2016-NE-06-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

    We received a report of an engine IFSD and subsequent undercowl 
fire on an IAE V2527-A5 turbofan engine during a revenue flight of an 
Airbus A320 airplane in September 2014. The subsequent investigation of 
this event determined that it was caused by a manufacturing defect in 
the HPT stage 2 hub that resulted in fracture and failure of the HPT 
stage 2 hub. The event involved release of a fir tree lug and two HPT 
stage 2 blades. IAE also identified a similar manufacturing defect on 
the HPT stage 1 hub. This condition, if not corrected, could result in 
uncontained HPT blade release, damage to the engine, and damage to the 
airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed IAE Non-Modification Service Bulletin (NMSB) No. V2500-
ENG-72-0661, Revision No. 1, dated February 5, 2016. The NMSB describes 
procedures for inspecting the HPT stage 1 and stage 2 hubs. This 
service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

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.

Proposed AD Requirements

    This proposed AD would require inspecting the engine HPT stage 1 
hub and HPT stage 2 hub, and, if necessary, their replacement with 
parts eligible for installation.

Costs of Compliance

    We estimate that this proposed AD affects 668 engines with 947 hubs 
installed on airplanes of U.S. registry. Some of the 668 engines have 
two hubs installed. We estimate that it would take about 8 hours per 
hub to perform the piece-part inspection. The average labor rate is $85 
per hour. We estimate that 568 hubs will require replacement. We 
estimate the pro-rated cost to replace an HPT stage 1 hub to be $50,271 
and the pro-rated cost to replace an HPT stage 2 hub to be $40,063. 
Based on these figures, we estimate the cost of this proposed AD on 
U.S. operators to be $26,298,816.

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 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 this 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 adding the following new airworthiness 
directive (AD):

International Aero Engines AG: Docket No. FAA-2016-4123; Directorate 
Identifier 2016-NE-06-AD.

(a) Comments Due Date

    We must receive comments by June 6, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to International Aero Engines AG (IAE) V2522-A5, 
V2524-A5,

[[Page 19518]]

V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and 
V2533-A5, engines with either of the following installed:
    (1) High-pressure turbine (HPT) stage 1 hub, part number (P/N) 
2A5001, with a serial number (S/N) listed in Table 1, Appendix A, of 
IAE Non-Modification Service Bulletin (NMSB) No. V2500-ENG-72-0661, 
Revision 1, dated February 5, 2016; or
    (2) HPT stage 2 hub, P/N 2A4802, with an S/N listed in Table 2, 
Appendix A, of IAE NMSB No. V2500-ENG-72-0661, Revision 1, dated 
February 5, 2016.

(d) Unsafe Condition

    This AD was prompted by the fracture of the HPT stage 2 hub 
during flight, which resulted in an in-flight shutdown, undercowl 
fire, and smoke in the cabin. We are issuing this AD to prevent 
failure of the HPT stage 1 or HPT stage 2 hubs, which could result 
in uncontained HPT blade 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) Inspect the HPT stage 1 hub, P/N 2A5001, and HPT stage 2 
hub, P/N 2A4802, at the next shop visit or as follows, whichever 
comes first:
    (i) For hubs with 0 to 7,000 CSN, before accumulating 13,000 
CSN;
    (ii) For hubs with 7,001 to 11,000 CSN, within 6,000 cycles from 
the effective date of this AD or before accumulating 15,000 CSN, 
whichever occurs first;
    (iii) For hubs with 11,001 to 15,500 CSN, within 4,000 cycles 
from the effective date of this AD or before accumulating 17,000 
CSN, whichever occurs first;
    (iv) For hubs with 15,501 CSN or greater, within 1,500 cycles 
from the effective date of this AD.
    (2) Use Accomplishment Instructions, paragraphs 2.A., 2.C., and 
2.D., of IAE NMSB No. V2500-ENG-72-0661, Revision 1, dated February 
5, 2016, to inspect the HPT stage 1 hub, P/N 2A5001.
    (3) Use Accomplishment Instructions, paragraphs 2.E., 2.G., and 
2H., of IAE NMSB No. V2500-ENG-72-0661, to inspect the HPT stage 2 
hub, P/N 2A4802.
    (4) Remove from service any HPT stage 1 hub, P/N 2A5001, or HPT 
stage 2 hub, P/N 2A4802, that fail the inspections required by 
paragraphs (e)(2) and (e)(3) of this AD, and replace with a part 
that is eligible for installation.

(f) Definition

    For the purpose of this AD, a ``shop visit'' is the induction of 
an engine into the shop for maintenance involving the separation of 
pairs of major mating engine flanges, except that the separation of 
engine flanges solely for the purposes of transportation without 
subsequent engine maintenance does not constitute an engine shop 
visit.

(g) 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].

(h) Related Information

    (1) For more information about this AD, contact Brian Kierstead, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7772; fax: 781-238-7199; email: 
[email protected].
    (2) For service information identified in this proposed AD, 
contact International Aero Engines AG, 400 Main Street, East 
Hartford, CT 06118; phone: 860-368-3700; fax: 860-368-4600; email: 
[email protected]; Internet: https://www.iaeworld.com.
    (3) 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.

    Issued in Burlington, Massachusetts, on March 24, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07579 Filed 4-4-16; 8:45 am]
BILLING CODE 4910-13-P