[Federal Register Volume 84, Number 121 (Monday, June 24, 2019)]
[Proposed Rules]
[Pages 29423-29426]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-13194]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0425; Product Identifier 2016-NE-13-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede airworthiness directive (AD) 
2016-24-08 which applies to all Rolls-Royce plc (RR) RB211-Trent 875-
17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-
Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 model 
turbofan engines. AD 2016-24-08 requires repetitive inspections of the 
engine upper fairing and repair or replacement of any fairing that 
fails inspection. Since the FAA issued AD 2016-24-08, RR has developed 
a modification of the engine upper bifurcation nose fairing assembly 
that terminates the inspection requirements of this AD. This proposed 
AD would continue the repetitive inspections until the terminating 
action is performed at the next engine shop visit. The FAA is proposing 
this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by August 8, 
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: 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 Rolls-
Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 
8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; internet: https://customers.rolls-royce.com/public/rollsroycecare. 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.

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-
0425; 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 NPRM, the mandatory continuing airworthiness information, 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: Eugene Triozzi, Aerospace Engineer, 
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 
781-238-7148; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2019-0425; 
Product Identifier 2016-NE-13-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. The FAA will 
consider all comments received by the closing date and may amend this 
NPRM because of those comments.
    The FAA will post all comments we receive, without change, to 
http://

[[Page 29424]]

www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact we receive about this proposed AD.

Discussion

    The FAA issued AD 2016-24-08, Amendment 39-18725 (81 FR 86567, 
December 1, 2016), (``AD 2016-24-08''), for all RR RB211-Trent 875-17, 
RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-
Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 model 
turbofan engines. AD 2016-24-08 requires repetitive inspections of the 
engine upper bifurcation fairing and repair or replacement of any 
fairing that fails inspection. AD 2016-24-08 resulted from reports of 
cracking and material release from an engine upper bifurcation fairing. 
The FAA issued AD 2016-24-08 to prevent failure of the engine fire 
protection system, engine fire, and damage to the airplane.

Actions Since AD 2016-24-08 Was Issued

    Since the FAA issued AD 2016-24-08, RR has developed a modification 
of the engine upper bifurcation nose fairing assembly. Performance of 
this modification terminates the repetitive inspection requirements of 
this AD. Also since the FAA issued AD 2016-24-08, the European Union 
Aviation Safety Agency (EASA) has issued AD 2018-0088, dated April 18, 
2018, which requires repetitive inspections of the engine upper 
bifurcation fairing until modification of the engine upper bifurcation 
nose fairing assembly at the next engine shop visit.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed RR Service Bulletin (SB) RB.211-72-J803, Revision 
1, dated July 13, 2018, and Initial Issue, dated December 7, 2017. This 
service information describes procedures for modification of the engine 
upper bifurcation nose fairing 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 RR Alert Non-Modification Service Bulletin (NMSB) 
RB.211-72-AJ165, Revision 2, dated August 21, 2018. This service 
information provides guidance on upper bifurcation fairing inspection 
locations. The FAA also reviewed AMM TASK 70-20-02, Water Washable 
Fluorescent Penetrant Inspection (Maintenance Process 213), and OMat 
632, high sensitivity fluorescent penetrant inspection. This service 
information provides guidance on performing a fluorescent penetrant 
inspection.

FAA's Determination

    The FAA is 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 retain the repetitive inspection 
requirements of AD 2016-24-08. This proposed AD would also require 
modification of the engine upper bifurcation nose fairing assembly at 
the next engine shop visit after the effective date of this AD.

Costs of Compliance

    The FAA estimates that this proposed AD affects 125 engines 
installed on airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection............................  3.25 work-hours x $85                 $0         $276.25         $34,531
                                         per hour = $276.25.
Modification of engine upper            2 work-hours x $85 per                50             220          27,500
 bifurcation nose fairing assembly.      hour = $170.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary repairs 
or replacements that would be required based on the results of the 
proposed inspection. The FAA has no way of determining the number of 
engines that might need these repairs or replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair of engine upper bifurcation fairing.  8 work-hours x $85 per hour = $680.            $500          $1,180
Replacement of engine upper bifurcation      30 work hours x $85 per hour =                  500           3,050
 fairing.                                     $2,550.
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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

[[Page 29425]]

applicable to engines, propellers, and associated appliances to the 
Manager, Engine and Propeller Standards Branch, Policy and Innovation 
Division.

Regulatory Findings

    The FAA has 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 that the proposed 
regulation:
    (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.

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 removing airworthiness directive (AD) 
2016-24-08, Amendment 39-18725 (81 FR 86567, December 1, 2016), and 
adding the following new AD:

Rolls-Royce plc: Docket No. FAA-2019-0425; Product Identifier 2016-
NE-13-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by August 8, 
2019.

(b) Affected ADs

    This AD replaces AD 2016-24-08, Amendment 39-18725 (81 FR 86567, 
December 1, 2016).

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211-Trent 875-17, 
RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-
Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 model 
turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7130, Engine 
Fireseals.

(e) Unsafe Condition

    This AD was prompted by reports of cracking and material release 
from an engine upper bifurcation fairing. The FAA is issuing this AD 
to prevent failure of the engine fire control system. The unsafe 
condition, if not addressed could result in engine fire and damage 
to the airplane.

(f) Compliance

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

(g) Required Actions

    (1) Within 7,500 engine flight hours (FHs) since new, or since 
the last inspection, or within 150 flight cycles (FCs) after the 
January 5, 2017 (the effective date of AD 2016-24-08), whichever 
occurs later, inspect the engine upper bifurcation fairing for 
cracks or missing material. Use paragraph (g)(3) of this AD to 
perform the inspection.
    (2) Repeat the inspection required by paragraph (g)(1) of this 
AD within every 7,500 engine FHs since last inspection.
    (3) Inspect the engine upper bifurcation fairing as follows.

    Note 1 to paragraph (g)(3):  Figure 1 of RR Alert Non-
Modification Service Bulletin (NMSB) RB.211-72-AJ165, Revision 2, 
dated August 21, 2018, provides guidance on upper bifurcation 
fairing inspection locations.

    (i) Visually inspect upper bifurcation fairing seal face 22, 
seal support 23, and Zone A for any cracks or material loss on the 
right side.
    (A) If fairing seal face 22 is found to have released material, 
repair or replace the fairing before further flight.
    (B) If there is a single crack found on fairing seal face 22, 
shorter than 6 mm, repair or replace the fairing within 100 engine 
FCs, or at the next shop visit, whichever occurs sooner.
    (C) If there is a single crack, longer than 6 mm, found on 
fairing seal face 22, repair or replace the fairing within 15 engine 
FCs or at the next shop visit, whichever occurs sooner.
    (D) If there are two or more cracks found on fairing seal face 
22, replace the fairing within 15 engine FCs or at next shop visit, 
whichever occurs sooner.
    (E) If there is any cracking or material loss found on seal 
support 23, replace the fairing within 15 engine FCs or at next shop 
visit, whichever occurs sooner.
    (ii) If the visual inspection required by paragraph (g)(3)(i) of 
this AD does not detect any cracks, fluorescent penetrant inspect 
Zone A.
    (A) If a crack shorter than 6 mm is detected, repair or replace 
the fairing within 100 engine FCs, or at the next shop visit, 
whichever occurs sooner.
    (B) If a crack longer than 6 mm is detected, repair or replace 
the fairing within 15 engine FCs or at the next shop visit, 
whichever occurs sooner.

    Note 2 to paragraph (g)(3)(ii):  AMM TASK 70-20-02, Water 
Washable Fluorescent Penetrant Inspection (Maintenance Process 213), 
and OMat 632, high sensitivity fluorescent penetrant inspection, 
provide guidance on performing a fluorescent penetrant inspection.

(h) Mandatory Terminating Action

    At the next engine shop visit after the effective date of this 
AD, modify the upper bifurcation fairing assembly in accordance with 
the Accomplishment Instructions, paragraph 3., of RR Service 
Bulletin (SB) RB.211-72-J803, Revision 1, dated July 13, 2018, or 
Original Issue, dated December 7, 2017. Installation of a modified 
upper bifurcation fairing assembly is terminating action to the 
inspections required by paragraphs (g)(1) through (g)(3) of this AD.

(i) Installation Prohibition

    After the effective date of this AD do not install an upper 
bifurcation fairing assembly, part number FK25470, onto any engine.

(j) Definition

    For the purpose of this AD, a ``shop visit'' is defined as 
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.

(k) 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 (l) 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.

(l) Related Information

    (1) For more information about this AD, contact Eugene Triozzi, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7148; fax: 781-238-7199; email: 
[email protected].
    (2) Refer to European Union Aviation Safety Agency (EASA) AD 
2018-0088, dated April 18, 2018 for more information. You may 
examine the EASA AD in the AD docket on the internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2019-0425.
    (3) For service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-
249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; 
internet: https://customers.rolls-royce.com/public/rollsroycecare. 
You may

[[Page 29426]]

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.

    Issued in Burlington, Massachusetts, on June 17, 2019.
Robert J. Ganley,
Manager, Engine & Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2019-13194 Filed 6-21-19; 8:45 am]
 BILLING CODE 4910-13-P