[Federal Register Volume 84, Number 158 (Thursday, August 15, 2019)]
[Rules and Regulations]
[Pages 41621-41623]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-17403]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0274; Product Identifier 2019-NE-07-AD; Amendment
39-19704; AD 2019-16-01]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines AG Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
International Aero Engines AG (IAE) V2525-D5 and V2528-D5 model
turbofan engines. This AD was prompted by reports of cracked turbine
exhaust cases (TECs). This AD requires initial and repetitive
inspections of the affected TEC and, depending on the results of the
inspections, its replacement with a part eligible for installation. The
FAA is issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective September 19, 2019.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
19, 2019.
ADDRESSES: For service information identified in this final rule,
contact International Aero Engines AG, 400 Main Street, East Hartford,
CT, 06118; phone: 800-565-0140; email: [email protected]; internet:
http://fleetcare.pw.utc.com. You may view this service information at
the FAA, Engine and Propeller Standards Branch, 1200 District Avenue,
Burlington, MA, 01803. For information on the availability of this
material at the FAA, call 781-238-7759. It is also available on the
internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0274.
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-2019-
0274; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Martin Adler, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone: 781-
238-7157; fax: 781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all IAE V2525-D5 and
V2528-D5 model turbofan engines. The NPRM published in the Federal
Register on May 20, 2019 (84 FR 22740). The NPRM was prompted by
reports of cracked TECs. The NPRM proposed to require initial and
repetitive inspections of the affected TEC and, depending on the
results of the inspections, its replacement with a part eligible for
installation. The FAA is issuing this AD to address the unsafe
condition on these products.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.
Request To Revise Compliance Time
IAE requested that the FAA revise the compliance time in paragraph
(g)(1) of this AD from 4,000 to 2,000 flight cycles after the effective
date of this AD. Considering that this AD will be effective in 2019,
IAE indicated that this change would better align the AD compliance
time with IAE's drawdown plan and the assumptions used in its safety
analysis.
The FAA disagrees. The FAA finds that the proposed compliance time
of 4,000 flight cycles after the effective date of this AD still meets
the safety objectives of this rule. Additionally, reducing the
compliance time from that proposed in the NPRM would likely require
that the FAA re-notice this AD, thereby further delaying its
implementation. The FAA did not change this AD.
Support for the AD
The Air Line Pilots Association International supported the NPRM as
written. The Boeing Company indicated it had no comment on the NPRM.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule as proposed.
Related Service Information Under 1 CFR Part 51
The FAA reviewed IAE Non-Modification Service Bulletin (NMSB)
V2500-ENG-72-0694, Revision No. 2, dated July 2, 2018. The NMSB
describes procedures for detecting any cracks that develop along the
rear mount stiffener rail on the TEC. 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.
[[Page 41622]]
Costs of Compliance
The FAA estimates that this AD affects 173 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspect turbine exhaust case.......... 3 work-hours x $85 per $0 $255 $44,115
hour = $255.
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The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
inspection. The FAA has no way of determining the number of aircraft
that might need this replacement:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Replace turbine exhaust case.................. 2 work-hours x $85 per hour = $725,000 $725,170
$170.
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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.
The FAA is 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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to engines, propellers, and
associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation Division.
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) Will not affect intrastate aviation in Alaska, and
(3) 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):
2019-16-01 International Aero Engines AG: Amendment 39-19704; Docket
No. FAA-2019-0274; Product Identifier 2019-NE-07-AD.
(a) Effective Date
This AD is effective September 19, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all International Aero Engines AG (IAE)
V2525-D5 and V2528-D5 model turbofan engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7250, Turbine
section.
(e) Unsafe Condition
This AD was prompted by reports of a cracked turbine exhaust
case (TEC). The FAA is issuing this AD to prevent failure of the
TEC. The unsafe condition, if not addressed, could result in engine
separation and loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) At the next engine shop visit, but not later than 4,000
flight cycles (FCs) after the effective date of this AD, perform an
eddy current inspection (ECI) and high sensitivity fluorescent
penetrant inspection (FPI) of the TEC front and rear mount stiffener
rails for cracking indications as follows:
(i) Perform an ECI using the Accomplishment Instructions, Part
I--For Engines Installed on Aircraft, paragraphs 2 through 19
inclusive, or Part II--For Engines Not Installed on Aircraft,
paragraphs 2 through 18 inclusive, of IAE Non-Modification Service
Bulletin (NMSB) V2500-ENG-72-0694, Revision No. 2, dated July 2,
2018 (``IAE NMSB V2500-ENG-72-0694'').
(ii) If a rejectable indication was found during the ECI,
perform a local high sensitivity FPI to confirm a crack.
[[Page 41623]]
(iii) If a rejectable indication was found during the ECI, but
no crack(s) were confirmed using the local high sensitivity FPI,
then clean, blend and repeat the ECI in the local area of the part.
Use the Accomplishment Instructions, Part I--For Engines Installed
on Aircraft, paragraph 20.A.(3), or Part II--For Engines Not
Installed on Aircraft, paragraph 19.A.(3), of IAE NMSB V2500-ENG-72-
0694 to perform the cleaning and blending. Use the Accomplishment
Instructions, Part I--For Engines Installed on Aircraft, paragraphs
2 through 19 inclusive, or Part II--For Engines Not Installed on
Aircraft, paragraphs 2 through 18 inclusive, of IAE NMSB V2500-ENG-
72-0694 to perform the repeat ECI.
(iv) If a rejectable indication was again found during the
repeat ECI, then repeat the local high sensitivity FPI inspection in
the local area of the part. If the local high sensitivity FPI does
not confirm a crack, follow the instructions in the Accomplishment
Instructions, Part I--For Engines Installed on Aircraft, paragraph
20.A.(5)(a), or Part II--For Engines Not Installed on Aircraft,
paragraph 19.A.(5)(a), of IAE NMSB V2500-ENG-72-0694.
(2) If no cracks were found, within 2,000 FCs since the last
inspection, and thereafter, repeat the inspections of paragraphs
(g)(1)(i) through (iv) of this AD.
(3) If a crack was confirmed during the FPI and visual
inspection required by paragraphs (g)(1)(ii) or (iv), before further
flight, remove the part from service and replace with a part
eligible for installation.
(h) Credit for Previous Actions
You may take credit for the inspections required by paragraph
(g)(1) of this AD if you performed these inspections before the
effective date of this AD, using IAE NMSB V2500-ENG-72-0694,
Revision No. 1, dated February 7, 2018; or IAE NMSB V2500-ENG-72-
0694, Original Issue, dated January 5, 2018.
(i) No Reporting Requirement
No reporting requirement contained within the NMSB referenced in
paragraph (g) of this AD is required by this AD.
(j) Definition
For the purpose of this AD, an ``engine shop visit'' is the
induction of an engine into the shop for maintenance involving the
separation of pairs of major mating engine case 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.
(k) Special Flight Permit
A special flight permit is not permitted if the crack indication
extends past the mount stiffener rail or if there is evidence of an
FPI indication on the outer diameter of the case.
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, ECO Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
certification office, send it to the attention of the person
identified in paragraph (m) of this AD. You may email your request
to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(m) Related Information
For more information about this AD, contact Martin Adler,
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA, 01803; phone: 781-238-7157; fax: 781-238-7199;
email: [email protected].
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) International Aero Engines Non-Modification Service Bulletin
V2500-ENG-72-0694, Revision No. 2, dated July 2, 2018.
(ii) [Reserved]
(3) For International Aero Engines service information
identified in this AD, contact International Aero Engines AG, 400
Main Street, East Hartford, CT, 06118; phone: 800-565-0140; email:
[email protected]; internet: http://fleetcare.pw.utc.com.
(4) You may view this referenced service information at the FAA,
Engine and Propeller Standards Branch, 1200 District Avenue,
Burlington, MA, 01803. For information on the availability of this
material at the FAA, call 781-238-7759.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on August 7, 2019.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification
Service.
[FR Doc. 2019-17403 Filed 8-14-19; 8:45 am]
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