AD 2019-16-01

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2019-17403]


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

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.

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

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: <a href="/cdn-cgi/l/email-protection#08606d64783a3c48787f267d7c6b266b6765"><span class="__cf_email__" data-cfemail="6109040d1153552111164f1415024f020e0c">[email&#160;protected]</span></a>; internet: 
<a href="http://fleetcare.pw.utc.com">http://fleetcare.pw.utc.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2019-0274.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#44092536302d2a6a0520282136042225256a232b32"><span class="__cf_email__" data-cfemail="bbf6dac9cfd2d595fadfd7dec9fbdddada95dcd4cd">[email&#160;protected]</span></a>.

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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspect turbine exhaust case..........  3 work-hours x $85 per                $0            $255         $44,115
                                         hour = $255.
----------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace turbine exhaust case..................  2 work-hours x $85 per hour =           $725,000        $725,170
                                                 $170.
----------------------------------------------------------------------------------------------------------------

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: <a href="/cdn-cgi/l/email-protection#15545b503854513854585a56557374743b727a63"><span class="__cf_email__" data-cfemail="f4b5bab1d9b5b0d9b5b9bbb7b4929595da939b82">[email&#160;protected]</span></a>.
    (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: <a href="/cdn-cgi/l/email-protection#db96baa9afb2b5f59abfb7bea99bbdbabaf5bcb4ad"><span class="__cf_email__" data-cfemail="e7aa8695938e89c9a6838b8295a7818686c9808891">[email&#160;protected]</span></a>.

(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: 
<a href="/cdn-cgi/l/email-protection#375f525b470503774740194243541954585a"><span class="__cf_email__" data-cfemail="38505d54480a0c78484f164d4c5b165b5755">[email&#160;protected]</span></a>; internet: <a href="http://fleetcare.pw.utc.com">http://fleetcare.pw.utc.com</a>.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    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]
 BILLING CODE 4910-13-P