Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 29423-29426 [2019-13194]
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Federal Register / Vol. 84, No. 121 / Monday, June 24, 2019 / Proposed Rules
(g) Requirements
Except as specified in paragraphs (h) and
(i) of this AD: Comply with all required
actions and compliance times specified in,
and in accordance with, EASA AD 2019–
0068.
(h) Exceptions to EASA AD 2019–0068
(1) For purposes of determining
compliance with the requirements of this AD:
Where EASA AD 2019–0068 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) Where EASA AD 2019–0068 specifies
credit for actions ‘‘accomplished before the
effective date of this AD in accordance with
the instructions of the applicable Airplane
Maintenance Manual,’’ this AD provides
credit for actions ‘‘accomplished before the
effective date of this AD in accordance with
the instructions of an FAA-approved
maintenance or inspection program.’’
(3) The ‘‘Remarks’’ section of EASA AD
2019–0068 does not apply to this AD.
(i) No Reporting Requirement
Although the service information
referenced in EASA AD 2019–0068 specifies
to submit certain information to the
manufacturer, this AD does not include that
requirement.
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(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards 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 International Section, send it
to the attention of the person identified in
paragraph (k)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(k) Related Information
(1) For information about EASA AD 2019–
0068, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; phone: +49
221 89990 6017; email: ADs@easa.europa.eu;
internet: www.easa.europa.eu. You may find
this EASA AD on the EASA website at
https://ad.easa.europa.eu. You may view this
EASA AD at the FAA, Transport Standards
Branch, 2200 South 216th St., Des Moines,
WA. For information on the availability of
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this material at the FAA, call 206–231–3195.
EASA AD 2019–0068 may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2019–0443.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–231–
3223.
Issued in Des Moines, Washington, on June
12, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–13048 Filed 6–21–19; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede airworthiness directive (AD)
2016–24–08 which applies to all RollsRoyce 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
https://www.regulations.gov. Follow the
instructions for submitting comments.
SUMMARY:
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29423
• 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: https://www.rollsroyce.com/contact/civil_team.jsp;
internet: https://customers.rollsroyce.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 https://
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: Eugene.triozzi@faa.gov.
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 https://
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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 NonModification 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
Action
Labor cost
Inspection ........................................................
Modification of engine upper bifurcation nose
fairing assembly.
3.25 work-hours × $85 per hour = $276.25 ...
2 work-hours × $85 per hour = $170 .............
The FAA estimates the following
costs to do any necessary repairs or
replacements that would be required
Cost per
product
Parts cost
based on the results of the proposed
inspection. The FAA has no way of
determining the number of engines that
$0
50
$276.25
220
Cost on U.S.
operators
$34,531
27,500
might need these repairs or
replacements:
ON-CONDITION COSTS
Action
Labor cost
Repair of engine upper bifurcation fairing ....................
Replacement of engine upper bifurcation fairing .........
8 work-hours × $85 per hour = $680 ...........................
30 work hours × $85 per hour = $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
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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
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Parts cost
$500
500
Cost per
product
$1,180
3,050
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
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Federal Register / Vol. 84, No. 121 / Monday, June 24, 2019 / Proposed Rules
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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.
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(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.
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(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
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29425
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: 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.
(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:
Eugene.triozzi@faa.gov.
(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 https://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:
https://www.rolls-royce.com/contact/civil_
team.jsp; internet: https://customers.rollsroyce.com/public/rollsroycecare. You may
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Federal Register / Vol. 84, No. 121 / Monday, June 24, 2019 / Proposed Rules
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0481; Product
Identifier 2019–NM–058–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for all
Airbus SAS Model A318 and A319
series airplanes; Model A320–211, –212,
–214, –216, –231, –232, and –233
airplanes; and Model A321–111, –112,
–131, –211, –212, –213, –231, and –232
airplanes. This proposed AD was
prompted by a report that during a
maintenance check, cracks were found
in a stiffener of a certain lateral window
frame. This proposed AD would require
repetitive high frequency eddy current
(HFEC) inspections for cracking of a
stiffener of a certain lateral window
frame, and applicable related
investigative and corrective actions, as
specified in a European Aviation Safety
Agency (EASA) AD, which will be
incorporated by reference. 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
https://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.
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SUMMARY:
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• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For the material identified in this
proposed AD that will be incorporated
by reference (IBR), contact the EASA, at
Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
89990 1000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find this IBR material on the EASA
website at https://ad.easa.europa.eu.
You may view this IBR material at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available in the AD docket on
the internet at https://
www.regulations.gov.
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–
0481; 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
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:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under the ADDRESSES section. Include
‘‘Docket No. FAA–2019–0481; Product
Identifier 2019–NM–058–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 based on
those comments.
The FAA will post all comments,
without change, to https://
www.regulations.gov, including any
personal information you provide. The
FAA will also post a report
summarizing each substantive verbal
contact the agency receives about this
NPRM.
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Discussion
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2019–0067, dated March 27, 2019
(‘‘EASA AD 2019–0067’’) (also referred
to as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus SAS Model A318 and
A319 series airplanes; Model A320–211,
–212, –214, –216, –231, –232, and –233
airplanes; and Model A321–111, –112,
–131, –211, –212, –213, –231, and –232
airplanes. The MCAI states:
Several occurrences were reported where,
during a maintenance check, cracks were
found at the lateral sliding window of the
fuselage FR4 [frame 4] upper attachment on
both RH [right-hand] and LH [left-hand]
sides.
This condition if not detected and
corrected, could reduce the structural
integrity of the fuselage.
To address this potential unsafe condition,
Airbus developed Airworthiness Limitation
Item (ALI) task 531105, providing
instructions for a detailed inspection (DET),
or a special detailed inspection (SDI) using
high frequency eddy current (HFEC) method.
Following further analysis of the reported
events, Airbus published the applicable
inspection SB [service bulletin], providing
instructions to accomplish the SDI, with
updated threshold and intervals, and not
allowing accomplishment of the DET as
alternative to the SDI.
For the reasons described above, this
[EASA] AD requires repetitive SDI of the
affected parts and, depending on findings,
accomplishment of applicable [related
investigative and] corrective action(s).
Related investigative actions include
an HFEC inspection and a detailed
visual inspection of the reworked area
to ensure a crack-free condition.
Corrective actions include reworking
the horizontal upper stiffener, a
modification (a cut-out of the sliding
window frame stiffener), and repair.
Related IBR Material Under 1 CFR Part
51
EASA AD 2019–0067 describes
procedures for repetitive HFEC
inspections of the horizontal upper
stiffener of the lateral window frame on
the RH and LH sides for any cracking,
and applicable related investigative and
corrective actions. This material 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.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
E:\FR\FM\24JNP1.SGM
24JNP1
]]>Agencies
[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]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 https://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: https://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 https://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
https://
[[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.
----------------------------------------------------------------------------------------------------------------
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 https://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: https://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
