[Federal Register Volume 84, Number 158 (Thursday, August 15, 2019)]
[Rules and Regulations]
[Pages 41617-41621]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-17417]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0465; Product Identifier 2018-NE-19-AD; Amendment 
39-19707; AD 2019-16-04]
RIN 2120-AA64


Airworthiness Directives; Engine Alliance Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-03-04 
for all Engine Alliance (EA) GP7270 and GP7277 model turbofan engines 
with a certain engine 1st-stage low-pressure compressor (LPC) rotor 
assembly, referred to after this as the ``engine fan hub assembly,'' 
installed. AD 2019-03-04 required a visual inspection of the engine fan 
hub assembly for damage, a one-time eddy current inspection (ECI) of 
the fan hub blade slot bottom and blade slot front edge for cracks, and 
removal of parts if damage or defects are found. For certain GP7270 and 
GP7277 model turbofan

[[Page 41618]]

engines, this AD continues to require a one-time ECI of the engine fan 
hub blade slot bottom and blade slot front edge for cracks and a visual 
inspection of the engine fan hub assembly for damage. For all GP7270 
and GP7277 model turbofan engines, this AD also requires an independent 
inspection of the engine fan hub assembly prior to reassembly of the 
engine fan hub blade lock assembly. For certain serial-numbered GP7270 
and GP7277 model turbofan engines, this AD requires replacement of the 
engine fan hub blade lock assembly. This AD was prompted by an 
uncontained failure of the engine fan hub. The FAA is issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective August 30, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 30, 
2019.
    The FAA must receive any comments on this AD by September 30, 2019.

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.
    For service information identified in this final rule, contact 
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 800-
565-0140; email: [email protected]; website: 
www.engineallianceportal.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-2019-0465.

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-
0465; 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 street address for Docket Operations is listed 
above. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Matthew Smith, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7735; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued AD 2019-03-04, Amendment 39-19556 (84 FR 4694, 
February 19, 2019), (``AD 2019-03-04''), for all EA GP7270 and GP7277 
model turbofan engines with a certain engine fan hub assembly 
installed. AD 2019-03-04 required a one-time ECI of the engine fan hub 
blade slot bottom and blade slot front edge for cracks, a visual 
inspection of the engine fan hub assembly for damage, and removal of 
parts if damage or defects are found that are outside serviceable 
limits. AD 2019-03-04 resulted from the FAA's determination that 
inspections need to be expanded to all EA GP7270 and GP7277 model 
turbofan engines with the affected engine fan hub assembly installed. 
The FAA issued AD 2019-03-04 to detect defects, damage, and cracks that 
could result in an uncontained failure of the engine fan hub assembly.

Actions Since AD 2019-03-04 was Issued

    Since the FAA issued AD 2019-03-04, the manufacturer determined the 
need to require an independent inspection of the fan hub assembly for 
damage prior to the reassembly of the engine fan hub blade lock 
assembly for all EA GP7270 and GP7277 model turbofan engines. The 
manufacturer also developed a new design of the engine fan hub blade 
lock assembly that decreases the potential for damage to the engine fan 
hub assembly when it is disassembled. The FAA is issuing this AD to 
address the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed EA ASB EAGP7-A72-389, Revision No. 4, dated June 
14, 2019. The ASB describes procedures for ECI and visual inspection of 
the GP7270 and GP7277 engine fan hub assembly. 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.

Other Related Service Information

    The FAA reviewed EA ASB EAGP7-A72-418, Revision No. 1, dated 
January 11, 2019. The ASB provides guidance on replacement or 
modification of the engine fan hub blade lock assembly.
    The FAA also reviewed the following service information:
    Subtask 72-31-42-210-001-A, of Task 72-31-42-000-802-A, from the 
A380 Aircraft Maintenance Manual (AMM). This subtask describes an on-
wing visual inspection that is to be performed after removal of the 
engine fan hub blade lock assembly.
    Figure 405 of Task 72-00-31-420-004 of the EA GP7000 Series Engine 
Manual (EM). This figure and task describe a visual inspection that is 
to be performed after removal of the engine fan hub blade lock assembly 
when the engine is in the shop.
    Subtask 72-00-00-210-012-A, of Task 72-00-00-210-806-A, from the 
A380 Aircraft Maintenance Manual (AMM). This subtask describes an on-
wing visual inspection that is to be performed after reassembly of the 
engine fan hub blade lock assembly.
    Task 72-00-31-420-004, Paragraph 1.E.(13), of the GP7000 Series EM 
describes a visual inspection that is to be performed after reassembly 
of the engine fan hub blade lock assembly when the engine is in the 
shop.
    Table 601 in Subtask 72-00-00-210-012-A, Task 72-00-00-210-806, 
from the A380 AMM or Task 72-00-31-220-010 of the EA GP7000 Series EM. 
Table 601 and Task 72-00-31-220-010 provide guidance on acceptable 
damage service limits.

FAA's Determination

    The FAA is issuing this AD because all the relevant information was 
evaluated and the FAA 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, for certain GP7270 and GP7277 model turbofan 
engines, a one-time ECI of the engine fan hub blade slot bottom and 
blade slot front edge for cracks and a visual inspection of the engine 
fan hub assembly for damage. For all GP7270 and GP7277 model turbofan 
engines, this AD also requires an independent inspection of the engine 
fan hub assembly prior to the reassembly of the engine fan hub blade 
lock assembly. For certain serial-

[[Page 41619]]

numbered GP7270 and GP7277 model turbofan engines, this AD requires 
replacement of the engine fan hub blade lock assembly with a part 
eligible for installation.

FAA's Justification and Determination of the Effective Date

    No domestic operators use this product. Therefore, the FAA finds 
good cause that notice and opportunity for prior public comment are 
unnecessary. In addition, for the reason stated above, the FAA finds 
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 the FAA did not provide you with notice and an opportunity 
to provide your comments before it becomes effective. However, the FAA 
invites you to send any written data, views, or arguments about this 
final rule. Send your comments to an address listed under the ADDRESSES 
section. Include the docket number FAA-2019-0465 and product identifier 
2018-NE-19-AD at the beginning of your comments. The FAA specifically 
invites comments on the overall regulatory, economic, environmental, 
and energy aspects of this final rule. The FAA will consider all 
comments received by the closing date and may amend this final rule 
because of those comments.
    The FAA will post all comments received, without change, to http://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this final rule.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects zero 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
----------------------------------------------------------------------------------------------------------------
ECI and visual inspection.............  14 work-hours x $85 per               $0          $1,190              $0
                                         hour = $1,190.
Replace fan hub blade lock assembly...  25 work-hours x $85 per           28,000          30,125               0
                                         hour = $2,125.
----------------------------------------------------------------------------------------------------------------

    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 engines 
that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace engine fan hub assembly...............  50 work-hours x $85 per hour =          $790,500        $794,750
                                                 $4,250.
----------------------------------------------------------------------------------------------------------------

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, and
    (2) Will not affect intrastate aviation in Alaska.

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 part 39 of the Federal Aviation 
Regulations (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.

[[Page 41620]]

Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
AD 2019-03-04, Amendment 39-19556 (84 FR 4694, February 19, 2019), and 
adding the following new AD:

2019-16-04 Engine Alliance: Amendment 39-19707; Docket No. FAA-2019-
0465; Product Identifier 2018-NE-19-AD.

(a) Effective Date

    This AD is effective August 30, 2019.

(b) Affected ADs

    This AD replaces AD 2019-03-04, Amendment 39-19556 (84 FR 4694, 
February 19, 2019).

(c) Applicability

    This AD applies to all Engine Alliance (EA) GP7270 and GP7277 
model turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7230, Turbine Engine 
Compressor Section.

(e) Unsafe Condition

    This AD was prompted by an uncontained failure of the engine fan 
hub. The FAA is issuing this AD to detect defects, damage, and 
cracks that could result in an uncontained failure of the engine fan 
hub assembly. The unsafe condition, if not addressed, could result 
in uncontained failure of the engine fan hub assembly, damage to the 
engine, and damage to the airplane.

(f) Compliance

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

(g) Required Actions

    (1) For EA GP7270 and GP7277 model turbofan engines, with engine 
fan hub assembly part numbers (P/Ns) 5760221 or 5760321, and with 
serial numbered engine fan hub assemblies identified in Planning 
Information, Table 4, in EA Alert Service Bulletin (ASB) EAGP7-A72-
389, Revision No. 4, dated June 14, 2019, within 3,000 cycles since 
new, or before further flight after the effective date of this AD, 
whichever occurs later:
    (i) For engine fan hub assemblies at the low-pressure compressor 
(LPC) module assembly level:
    (A) Perform a visual inspection of the engine fan hub assembly, 
in accordance with the Accomplishment Instructions, For Fan Hubs at 
LPC Module Assembly Level, paragraphs 1.A.(1), 1.A.(4), and 
1.A.(6)(a), of EA ASB EAGP7-A72-389, Revision No. 4, dated June 14, 
2019.
    (B) Perform an eddy current inspection (ECI) of the engine fan 
hub blade slot bottoms and front edges in accordance with the 
Accomplishment Instructions, For Fan Hubs at LPC Module Assembly 
Level, paragraphs 2.A and 2.B, of EA ASB EAGP7-A72-389, Revision No. 
4, dated June 14, 2019.
    (ii) For engine fan hub assemblies at the piece part level:
    (A) Perform a visual inspection of the engine fan hub assembly, 
in accordance with the Accomplishment Instructions, For Fan Hubs at 
Piece Part Level, paragraphs 1.A.(1) and 1.A.(3), of EA ASB EAGP7-
A72-389, Revision No. 4, dated June 14, 2019.
    (B) Perform an ECI of the engine fan hub blade slot bottoms and 
front edges, in accordance with the Accomplishment Instructions, For 
Fan Hubs at Piece Part Level, paragraphs 2.A and 2.B, of EA ASB 
EAGP7-A72-389, Revision No. 4, dated June 14, 2019.
    (iii) For engine fan hub assemblies installed in an engine (on-
wing or off-wing):
    (A) Perform a visual inspection of the engine fan hub assembly, 
in accordance with the Accomplishment Instructions, For Fan Hubs 
Installed in an Engine, paragraphs 1.C.(1), 1.C.(5), and 1.C.(7)(a), 
of EA ASB EAGP7-A72-389, Revision No. 4, dated June 14, 2019.
    (B) Perform an ECI of the engine fan hub blade slot bottoms and 
front edges, in accordance with the Accomplishment Instructions, For 
Fan Hubs Installed in an Engine, paragraphs 1.D.(1) and 1.D.(2), of 
EA ASB EAGP7-A72-389, Revision No. 4, dated June 14, 2019.
    (iv) If the engine fan hub assembly visual inspection reveals 
defects or damage to the engine fan hub assembly outside the 
serviceable limits specified in Table 6 in the Accomplishment 
Instructions of EA ASB EAGP7-A72-389, Revision No. 4, dated June 14, 
2019, before further flight, remove the engine fan hub assembly from 
service and replace with a part eligible for installation.
    (v) If the engine fan hub assembly ECI results in a rejectable 
indication per the Appendix, Added Data, of EA ASB EAGP7-A72-389, 
Revision No. 4, dated June 14, 2019, remove the engine fan hub 
assembly from service and, before further flight, replace with a 
part that is eligible for installation.
    (2) For all GP7270 and GP7277 model turbofan engines, after the 
effective date of this AD:
    (i) At the next disassembly of the engine fan hub blade lock 
assembly, visually inspect the following areas for damage:
    (A) The fan hub blade lock retention hooks (also known as lock 
ring contact area); and
    (B) The fan hub rim face.
    (ii) At the next reassembly of the fan hub blade lock assembly, 
visually inspect the following areas of the engine fan hub for 
damage:
    (A) The fan hub scallop areas;
    (B) The fan hub bore area behind the balance flange;
    (C) The fan hub fan blade lock retention hooks;
    (D) The fan hub rim face; and
    (E) The clinch nut holes.
    (iii) After any reassembly per paragraph (g)(2)(ii), before 
further flight, perform an independent inspection of all areas of 
the engine fan hub referenced in paragraph (g)(2)(ii) of this AD for 
damage.
    (iv) Thereafter, repeat inspections as required by paragraph 
(g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD at each 
disassembly and reassembly of the engine fan hub blade lock 
assembly.
    (v) As an optional terminating action to the inspection 
requirements and independent inspection requirements of paragraph 
(g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD, insert the 
requirements for the visual inspections and independent inspections 
required by these paragraphs as Required Inspection Items in the 
approved continuous airworthiness maintenance program for the 
airplane.
    (vi) If damage is found outside serviceable limits as the result 
of the inspections required by (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) 
of this AD, before further flight, remove the engine fan hub 
assembly from service and replace with a part eligible for 
installation.
    (3) For GP7270 and GP7277 model turbofan engines with engine 
serial numbers P550101 through P550706, remove the engine fan hub 
blade lock assembly, P/N 5700451, by September 1, 2020, and replace 
with a part eligible for installation. Refer to EA ASB EAGP7-A72-
418, Revision No. 1, dated January 11, 2019, for guidance on 
replacement of the engine fan hub blade lock assembly.

(h) Credit for Previous Actions

    You may take credit for the inspection required by paragraph 
(g)(1) of this AD if you performed the inspection before the 
effective date of this AD using EA ASB EAGP7-A72-389, Revision No. 
3, dated October 18, 2018, or an earlier version.

(i) Definitions

    (1) For the purpose of this AD, a part eligible for installation 
for replacement of the engine fan hub blade lock assembly is:
    (i) A part that is not P/N 5700451, or
    (ii) An engine fan hub blade lock assembly that has been 
modified in accordance with EA ASB EAGP7-A72-418, Revision No. 1, 
dated January 11, 2019 or EA ASB EAGP7-A72-418, Revision No. 0, 
dated December 7, 2018.
    (2) For the purpose of this AD, an independent inspection is a 
second inspection performed by an individual qualified to perform 
inspections who was not involved in the original inspection of the 
engine fan hub assembly following disassembly and reassembly of the 
engine fan hub blade lock assembly.

(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: [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.
    (3) AMOCs approved for AD 2018-11-16 (83 FR 27891, June 15, 
2018) and AD 2019-03-04 (84 FR 4694, February 19, 2019) are

[[Page 41621]]

approved as AMOCs for the corresponding provisions of this AD.

(k) Related Information

    For more information about this AD, contact Matthew Smith, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7735; fax: 781-238-7199; email: 
[email protected].

(l) 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) Engine Alliance (EA) Alert Service Bulletin EAGP7-A72-389, 
Revision No. 4, dated June 14, 2019.
    (ii) [Reserved]
    (3) For EA service information identified in this AD, contact 
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 
800-565-0140; email: [email protected]; website: 
www.engineallianceportal.com.
    (4) You may view this service information at the FAA, Engine & 
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 9, 2019.
Karen M. Grant,
Acting Manager, Engine & Propeller Standards Branch, Aircraft 
Certification Service.
[FR Doc. 2019-17417 Filed 8-14-19; 8:45 am]
 BILLING CODE 4910-13-P