[Federal Register Volume 85, Number 52 (Tuesday, March 17, 2020)]
[Rules and Regulations]
[Pages 15054-15056]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-05330]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0614; Product Identifier 2019-NE-14-AD; Amendment 
39-19878; AD 2020-05-28]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines LLC Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-11-08 
for all International Aero Engines, LLC (IAE) PW1133G-JM, PW1133GA-JM, 
PW1130G-JM, PW1129G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-
JM, PW1124G1-JM, and PW1122G-JM model turbofan engines. AD 2019-11-08 
required the removal of the main gearbox (MGB) assembly and electronic 
engine control (EEC) software and the installation of a part and 
software version eligible for installation for engines that operate on 
extended operations (ETOPS) flights. This AD retains the requirements 
of AD 2019-11-08 and requires replacement of the MGB assembly and EEC 
software on engines that do not operate on ETOPS flights. This AD was 
prompted by multiple reports of in-flight engine shutdowns as the 
result of high-cycle fatigue causing fracture of certain parts of the 
MGB assembly. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective April 21, 2020.

ADDRESSES: For service information identified in this final rule, 
contact International Aero Engines, LLC, 400 Main Street, East 
Hartford, CT, 06118; phone: 800-565-0140; email: help24@pw.utc.com; 
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.

[[Page 15055]]

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0614; 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: Kevin M. Clark, Aerospace Engineer, 
ECO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone: 
781-238-7088; fax: 781-238-7199; email: kevin.m.clark@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2019-11-08, Amendment 39-19654 (84 FR 
27511, June 13, 2019), (``AD 2019-11-08''). AD 2019-11-08 applied to 
all IAE PW1133G-JM, PW1133GA-JM, PW1130G-JM, PW1129G-JM, PW1127G-JM, 
PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM, and PW1122G-JM model 
turbofan engines. AD 2019-11-08 required the removal of the MGB 
assembly and EEC software and the installation of a part and software 
version eligible for installation for engines that operate on ETOPS 
flights. AD 2019-11-08 was prompted by multiple reports of in-flight 
engine shutdowns as the result of high-cycle fatigue causing fracture 
of certain parts of the MGB assembly.
    The NPRM published in the Federal Register on October 4, 2019 (84 
FR 53082). The actions in AD 2019-11-08 were interim and only addressed 
engines that operate on 180-minute or 120-minute ETOPS flights. The 
NPRM proposed to retain and revise the compliance time for those 
actions and add requirements to replace the MGB assembly and EEC 
software on affected engines that do not operate on ETOPS flights. 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 AD. The following presents the comment received on the 
NPRM and the FAA's response to the comment.

Request To Consider Loss of Load

    An anonymous commenter asked if an assessment had been made to the 
loss of load and associated possible low-pressure turbine (LPT) 
overspeed and disk burst when the MGB components fail due to high-cycle 
fatigue.
    The FAA does not agree. The FAA did not perform an assessment of 
the low-pressure turbine overspeed and disk burst due to the loss of 
load of the main gearbox because the failure of the MGB components 
cannot lead directly to an LPT overspeed without some other extremely 
remote failure of the engine occurring simultaneously. The main rotor 
speeds of the engine are normally controlled by the engine control 
system and further protected against overspeed due to abnormal 
operation by an independent overspeed protection system. The failure of 
an MGB component will not affect either the normal engine control or 
the overspeed protection system from safely controlling the rotor 
speeds. Further, the MGB is powered by the high-pressure rotor system 
and has no effect on the low-pressure rotor speed. No change to this AD 
is required.

Updates to Service Information

    Since the FAA published the NPRM, IAE has updated its service 
information. The FAA has therefore updated the references to the 
service information from the original issue discussed in the NPRM to 
Issue No. 004 in this AD.

Conclusion

    The FAA reviewed the relevant data, considered the comment 
received, and determined that air safety and the public interest 
require adopting this AD as proposed.

Related Service Information

    The FAA reviewed Pratt & Whitney (PW) Service Bulletin (SB) 
PW1000G-C-72-00-0129-00A-930A-D, Issue No. 004, dated January 7, 2020, 
and PW SB PW1000G-C-73-00-0037-00A-930A-D, Issue No. 004, dated 
November 4, 2019. PW SB PW1000G-C-72-00-0129-00A-930A-D, Issue No. 004, 
dated January 7, 2020, contains procedures for replacing the integrated 
drive generator oil pump drive gearshaft assembly in the MGB assembly. 
PW SB PW1000G-C-73-00-0037-00A-930A-D, Issue No. 004, dated November 4, 
2019, contains procedures for replacing the EEC software to incorporate 
FCS5.0 software.

Costs of Compliance

    The FAA estimates that this AD affects 72 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
----------------------------------------------------------------------------------------------------------------
Replace the MGB assembly..............  13 work-hours x $85 per          $75,000         $76,105      $5,479,560
                                         hour = $1,105.
Replace the EEC software..............  3 work-hours x $85 per                 0             255          18,360
                                         hour = $255.
----------------------------------------------------------------------------------------------------------------

    The new requirements of this AD add no additional economic burden.

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.

Regulatory Findings

    The FAA has determined that 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

[[Page 15056]]

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 removing Airworthiness Directive (AD) 
2019-11-08, Amendment 39-19654 (84 FR 27511, June 13, 2019), and adding 
the following new AD:

2020-05-28 International Aero Engines LLC: Amendment 39-19878; 
Docket No. FAA-2019-0614; Product Identifier 2019-NE-14-AD.

(a) Effective Date

    This AD is effective April 21, 2020.

(b) Affected ADs

    This AD replaces AD 2019-11-08, Amendment 39-19654 (84 FR 27511, 
June 13, 2019).

(c) Applicability

    This AD applies to all International Aero Engines, LLC (IAE) 
PW1133G-JM, PW1133GA-JM, PW1130G-JM, PW1129G-JM, PW1127G-JM, 
PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM, and PW1122G-JM 
model turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7260, Turbine Engine 
Accessory Drive.

(e) Unsafe Condition

    This AD was prompted by multiple reports of in-flight engine 
shutdowns as the result of high-cycle fatigue causing fracture of 
certain parts of the main gearbox (MGB) assembly. The FAA is issuing 
this AD to prevent failure of the MGB assembly. The unsafe 
condition, if not addressed, could result in failure of one or more 
engines, loss of thrust control, and loss of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Remove the MGB assembly, part number (P/N) 5322505, and 
install a part eligible for installation as follows:
    (i) For engines that operate on 180-minute extended operations 
(ETOPS) flights, before further flight after the effective date of 
this AD.
    (ii) For engines that operate on 120-minute ETOPS flights, 
within 120 days from June 28, 2019 (the effective date of AD 2019-
11-08), or before further flight after the effective date of this 
AD, whichever occurs later.
    (iii) For engines that do not operate on ETOPS flights, at the 
next engine shop visit after the effective date of this AD.
    (2) For engines with MGB assembly P/N 5322505, within 120 days 
from June 28, 2019 (the effective date of AD 2019-11-08), or before 
further flight after the effective date of this AD, whichever occurs 
later, remove electronic engine control (EEC) software earlier than 
FCS5.0 from the engine and install EEC software that is eligible for 
installation.

(h) Installation Prohibition

    (1) After the effective date of this AD, do not install 
integrated drive generator (IDG) oil pump drive gearshaft assembly, 
P/N 5322630-01, into an MGB assembly.
    (2) After the effective date of this AD, do not load EEC 
software earlier than FCS5.0 on any engine identified in paragraph 
(c) of this AD with an MGB assembly, P/N 5322505.

(i) Definitions

    (1) For the purpose of this AD, a ``part eligible for 
installation'' is an MGB assembly with an IDG oil pump drive 
gearshaft assembly other than P/N 5322630-01.
    (2) 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 flanges, except that the 
separation of engine flanges solely for the purposes of 
transportation of the engine without subsequent engine maintenance 
does not constitute an engine shop visit.
    (3) For the purpose of this AD, ``EEC software that is eligible 
for installation'' is EEC software FCS5.0 and later.

(j) 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 (k) of this AD. You may email your request 
to: ANE-AD-AMOC@faa.gov.
    (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.

(k) Related Information

    For more information about this AD, contact Kevin M. Clark, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA, 01803; phone: 781-238-7088; fax: 781-238-7199; 
email: kevin.m.clark@faa.gov.

(l) Material Incorporated by Reference

    None.

    Issued on March 11, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-05330 Filed 3-16-20; 8:45 am]
 BILLING CODE 4910-13-P


