Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines, 24236-24239 [2017-10437]
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Federal Register / Vol. 82, No. 101 / Friday, May 26, 2017 / Rules and Regulations
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intended to protect the airplane and its
occupants if failure occurs.
Special conditions 3, 7, and 8 are selfexplanatory.
Special condition no. 4 makes it clear
that the flammable fluid fire protection
requirements of § 25.863 apply to nonrechargeable lithium battery
installations. Section 25.863 is
applicable to areas of the airplane that
could be exposed to flammable fluid
leakage from airplane systems. Nonrechargeable lithium batteries contain
an electrolyte that is a flammable fluid.
Special condition no. 5 requires that
each non-rechargeable lithium battery
installation not damage surrounding
structure or adjacent systems,
equipment, or electrical wiring from
corrosive fluids or gases that may escape
in such a way as to cause a major or
more severe failure condition.
While special condition no. 5
addresses corrosive fluids and gases,
special condition no. 6 addresses heat.
Special condition no. 6 requires that
each non-rechargeable lithium battery
installation have provisions to prevent
any hazardous effect on airplane
structure or systems caused by the
maximum amount of heat the battery
installation can generate due to any
failure of it or its individual cells. The
means of meeting special conditions
nos. 5 and 6 may be the same, but the
requirements are independent and
address different hazards.
These special conditions apply to all
non-rechargeable lithium battery
installations in lieu of § 25.1353(b)(1)
through (4) at Amendment 25–123 or
§ 25.1353(c)(1) through (4) at earlier
amendments. Those regulations remain
in effect for other battery installations.
These special conditions contain the
additional safety standards that the
Administrator considers necessary to
establish a level of safety equivalent to
that established by the existing
airworthiness standards.
Applicability
These special conditions are
applicable to the 787–9 series airplanes.
Should Boeing apply at a later date for
a change to the type certificate to
include another model incorporating the
same novel or unusual design feature,
these special conditions would apply to
that model as well.
These special conditions are only
applicable to design changes applied for
after the effective date.
These special conditions are not
applicable to changes to previously
certified non-rechargeable lithium
battery installations where the only
change is either cosmetic or to relocate
the installation to improve the safety of
VerDate Sep<11>2014
17:49 May 25, 2017
Jkt 241001
the airplane and occupants. Previously
certified non-rechargeable lithium
battery installations, as used in this
paragraph, are those installations
approved for certification projects
applied for on or before the effective
date of these special conditions. A
cosmetic change is a change in
appearance only, and does not change
any function or safety characteristic of
the battery installation. These special
conditions are also not applicable to
unchanged, previously certified nonrechargeable lithium battery
installations that are affected by a
change in a manner that improves the
safety of its installation. The FAA
determined that these exclusions are in
the public interest because the need to
meet all of the special conditions might
otherwise deter these design changes
that improve safety.
Conclusion
This action affects only a certain
novel or unusual design feature on one
model of airplane. It is not a rule of
general applicability.
The substance of these special
conditions has been subjected to the
notice and comment period in prior
instances and has been derived without
substantive change from those
previously issued. It is unlikely that
prior public comment would result in a
significant change from the substance
contained herein. Therefore, the FAA
has determined that prior public notice
and comment are unnecessary and
impracticable, and good cause exists for
adopting these special conditions upon
publication in the Federal Register. The
FAA is requesting comments to allow
interested persons to submit views that
may not have been submitted in
response to the prior opportunities for
comment described above.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the following special
conditions are issued as part of the type
certification basis for the Boeing Model
787–9 series airplanes.
Non-Rechargeable Lithium Battery
Installations
In lieu of § 25.1353(b)(1) through (4)
at Amendment 25–123 or § 25.1353(c)(1)
through (4) at earlier amendments, each
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non-rechargeable lithium battery
installation must:
1. Be designed to maintain safe cell
temperatures and pressures under all
foreseeable operating conditions to
prevent fire and explosion.
2. Be designed to prevent the
occurrence of self-sustaining,
uncontrollable increases in temperature
or pressure.
3. Not emit explosive or toxic gases,
either in normal operation or as a result
of its failure, that may accumulate in
hazardous quantities within the
airplane.
4. Meet the requirements of § 25.863.
5. Not damage surrounding structure
or adjacent systems, equipment, or
electrical wiring from corrosive fluids or
gases that may escape in such a way as
to cause a major or more severe failure
condition.
6. Have provisions to prevent any
hazardous effect on airplane structure or
systems caused by the maximum
amount of heat it can generate due to
any failure of it or its individual cells.
7. Have a failure sensing and warning
system to alert the flightcrew if its
failure affects safe operation of the
airplane.
8. Have a means for the flightcrew or
maintenance personnel to determine the
battery charge state if the battery’s
function is required for safe operation of
the airplane.
Note: A battery system consists of the
battery and any protective, monitoring, and
alerting circuitry or hardware inside or
outside of the battery. It also includes vents
(where necessary) and packaging. For the
purpose of these special conditions, a
‘‘battery’’ and ‘‘battery system’’ are referred to
as a battery.
Issued in Renton, Washington, on May 17,
2017.
Michael Kaszycki,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10843 Filed 5–25–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0186; Directorate
Identifier 2017–NE–07–AD; Amendment 39–
18899; AD 2017–10–25]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG Turbofan
Engines
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Federal Register / Vol. 82, No. 101 / Friday, May 26, 2017 / Rules and Regulations
Final rule; request for
comments.
ACTION:
FOR FURTHER INFORMATION CONTACT:
We are adopting a new
airworthiness directive (AD) for all
Rolls-Royce Deutschland Ltd & Co KG
(RRD) model Spey 506–14A, Spey 555–
15, Spey 555–15H, Spey 555–15N, and
Spey 555–15P turbofan engines. This
AD requires reducing the maximum
approved life limits for certain highpressure compressor (HPC) stage 12
rotor disks. We are issuing this AD to
correct the unsafe condition on these
products.
SUMMARY:
This AD becomes effective June
12, 2017.
We must receive comments on this
AD by July 10, 2017.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Mail: U.S. Department of
Transportation, 1200 New Jersey
Avenue SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: 202–493–2251.
For service information identified in
this AD, contact Rolls-Royce
Deutschland Ltd & Co KG, Eschenweg
11–15827 Dahlewitz, BlankenfeldeMahlow, Germany; phone: +49 0 33–
7086–1944; fax: +49 0 33–7086–3276.
You may view this service information
at the FAA, Engine & Propeller
Directorate, 1200 District Avenue,
Burlington, MA 01803. For information
on the availability of this material at the
FAA, call 781–238–7125.
DATES:
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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–2017–
0186; or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the mandatory
continuing airworthiness information
(MCAI), regulatory evaluation, any
comments received, and other
information. The address for the Docket
Office (phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
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Jkt 241001
Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7754; fax: 781–238–7199;
email: robert.green@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2017–0186;
Directorate Identifier 2017–NE–07–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD 2017–
0014, dated January 30, 2017 (referred to
hereinafter as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
Based on revised stress analysis and life
calculation, Rolls-Royce Deutschland (RRD)
determined new provisional life limits for
high pressure compressor (HPC) stage 12
rotor disks, Part Number (P/N) EU25917, P/
N EU56963, P/N JR10242 and P/N JR18449,
reducing the maximum approved life limits
currently defined in the RRD Spey 555–15
Engine Maintenance Manual (EMM), Chapter
5–10–1, currently at the revision dated July
2015 and the Engine Overhaul Manual
(EOM), Chapter 5–10, revision dated
November 2014. The Spey 506–14A EMM,
Chapter 5–10–1 revision dated October 1993
as well as the Spey 506–14A EOM, Chapter
5–10 revision dated November 1992 already
contain the applicable life limit. Failure to
replace an affected HPC stage 12 rotor disk
before exceeding these limits, could lead to
an uncontained engine failure, possibly
resulting in damage to, and/or reduced
control of, the aeroplane. To address this
potential unsafe condition, RRD issued Alert
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Non-Modification Service Bulletin (NMSB)
Sp72–A1071 to provide instructions to
determine (re-calculate) the consumed and
remaining service life for each part. For the
reasons described above, this AD requires recalculation of the service life (consumed and
remaining) of the affected HPC stage 12 rotor
disks and, depending on the results,
implementation of the life limits. It is
expected that the affected reduced life limits
are introduced into a next revision of the
RRD Spey 555–15 Engine EMM and EOM.
You may obtain further information
by examining the MCAI in the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0186.
Related Service Information
RRD has issued Alert NonModification Service Bulletin (NMSB)
Sp72–A1071, Revision 1, dated January
27, 2017. The Alert NMSB provides
instructions to re-calculate the
consumed and remaining service life for
HPC stage 12 rotor disks, part number
(P/N) EU25917, P/N EU56963, P/N
JR10242, and P/N JR18449. This service
information is available by the means
identified in the ADDRESSES section.
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of Germany, and
is approved for operation in the United
States. Pursuant to our bilateral
agreement with the European
Community, EASA has notified us of
the unsafe condition described in the
MCAI. We are issuing this AD because
we evaluated all information provided
by EASA and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design. This AD requires reducing
the maximum approved life limits and
re-calculating the consumed and
remaining service life for HPC stage 12
rotor disks P/N EU25917, P/N EU56963,
P/N JR10242, and P/N JR18449.
FAA’s Determination of the Effective
Date
No domestic operators use this
product. Therefore, we find that notice
and opportunity for prior public
comment are unnecessary and that good
cause exists for making this amendment
effective in less than 30 days.
Costs of Compliance
We estimate that this AD affects 0
engines installed on airplanes of U.S.
registry. We estimate the following costs
to comply with this AD:
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Federal Register / Vol. 82, No. 101 / Friday, May 26, 2017 / Rules and Regulations
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
Pro-rated lost life ....................
1 work-hour × $85 per hour = $85 .........................................
$3,900
$3,985
$0
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.
We are 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.
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Regulatory Findings
We 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 power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction, and
(4) 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.
VerDate Sep<11>2014
17:49 May 25, 2017
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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
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 adding
the following new airworthiness
directive (AD):
■
2017–10–25 Rolls-Royce Deutschland Ltd &
Co KG: Amendment 39–18899; Docket
No. FAA–2017–0186; Directorate
Identifier 2017–NE–07–AD.
(a) Effective Date
This AD is effective June 12, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Rolls-Royce
Deutschland Ltd & Co KG (RRD) Spey 506–
14A, Spey 555–15, Spey 555–15H, Spey 555–
15N, and Spey 555–15P turbofan engines
with high-pressure compressor (HPC) stage
12 rotor disks, part number (P/N) EU25917,
P/N EU56963, P/N JR10242, or P/N JR18449,
installed.
(d) Subject
Joint Aircraft System Component (JASC)
7230, Turbine Engine Compressor Section.
(e) Reason
This AD was prompted by RRD recalculating the life limits for HPC stage 12
rotor disks, P/N EU25917, P/N EU56963, P/
N JR10242, and P/N JR18449. We are issuing
this AD to prevent failure of the HPC stage
12 rotor disk, uncontained HPC stage 12 rotor
disk release, 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) Within 30 days after the effective date
of this AD, determine if:
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(i) The affected part was ever operated in
a Spey 555–15, Spey 555–15H, Spey 555–
15N, or Spey 555–15P engine model, or
(ii) the affected part was operated soley in
a Spey 506–14A engine.
(2) If the affected part was operated solely
in a Spey 506–14A engine with no history of
operating in a Spey 555–15, Spey 555–15H,
Spey 555–15N, or Spey 555–15P engine, no
further action is required.
(3) If the affected part was operated in in
both Spey 506–14A and Spey 555–15, Spey
555–15H, Spey 555–15N, or Spey 555–15P
engine models, or solely in Spey 555–15,
Spey 555–15H, Spey 555–15N, or Spey 555–
15P engines, re-calculate the consumed
cyclic life (and remaining service life) using
the Maximum Approved Life for each engine
model and take-off monitoring procedure as
defined in Figures 1 and 2 to paragraph (g)
of this AD.
(4) After the effective date of this AD, the
Maximum Approved Lives for the affected
parts are as defined in Figure 2 to paragraph
(g) of this AD. Calculate the consumed cyclic
life (and remaining service life) using the
Spey 555–15, Spey 555–15H, Spey 555–15N,
or Spey 555–15P Maximum Approved Lives
in Figure 2 to paragraph (g) of this AD.
(5) For Spey 506–14A engines with an
affected part installed, that do not have an
engine shop visit after the effective date of
this AD before the re-calculated consumed
cyclic life of the affected part exceeds 14,700
flight cycles (FC), remove the affected part
from service before the re-calculated
consumed cyclic life exceeds 14,700 FC, or
50 FC or 30 days after the effective date of
this AD, whichever occurs later.
(6) For Spey 555–15, Spey 555–15H, Spey
555–15N, or Spey 555–15P engines with an
affected part installed, that do not have an
engine shop visit after the effective date of
this AD before the re-calculated consumed
cyclic life of the affected part exceeds the
Maximum Approved Lives in Figure 2 to
paragraph (g) of this AD, remove the affected
part from service before the re-calculated
consumed cyclic life exceeds the later of the
following:
(i) Maximum Approved Lives in Figure 2
to paragraph (g) of this AD, or
(ii) 200 FC or 90 days after the effective
date of this AD, or before exceeding the InService Replacement Limits defined in
Figure 3 to paragraph (g) of this AD,
whichever occurs first.
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Federal Register / Vol. 82, No. 101 / Friday, May 26, 2017 / Rules and Regulations
FIGURE 1 TO PARAGRAPH (g)—SPEY 506–14A HIGH-PRESSURE COMPRESSOR (HPC) STAGE 12 ROTOR DISK MAXIMUM
APPROVED LIFE
Flight cycles
HPC stage 12 rotor disk, P/N EU25917, EU56963, and JR10242 ...............................................................................................
14,700
FIGURE 2 TO PARAGRAPH (g)—SPEY 555–15, SPEY 555–15H, SPEY 555–15N, OR SPEY 555–15P HPC STAGE 12
ROTOR DISK, P/N EU25917, EU56963, JR10242, AND JR18449, MAXIMUM APPROVED LIFE
Maximum
approved lives
(flight cycles)
Take-off monitoring procedure
(A) With no high-pressure (HP) revolutions per minute (RPM) monitoring ..................................................................................
HP RPM monitoring; stated RPM not exceeded on more than 15% of occasions:
(B) 100% N2 ...........................................................................................................................................................................
(C) 99% N2 .............................................................................................................................................................................
(D) 98% N2 .............................................................................................................................................................................
(E) 97% N2 .............................................................................................................................................................................
(F) No HP RPM monitoring required Datum (Average N2 at 99.5%) ...........................................................................................
11,500
13,600
17,100
19,300
20,500
16,800
FIGURE 3 TO PARAGRAPH (g)—SPEY 555–15, SPEY 555–15H, SPEY 555–15N, OR SPEY 555–15P HPC STAGE 12
ROTOR DISK, P/N EU25917, EU56963, JR10242, AND JR18449, IN-SERVICE REPLACEMENT LIMITS
In-service
replacement limits
(flight cycles)
Take-off monitoring procedure
(A) With no HP RPM monitoring ...................................................................................................................................................
HP RPM monitoring; stated RPM not exceeded on more than 15% of occasions:
(B) 100% N2 ...........................................................................................................................................................................
(C) 99% N2 .............................................................................................................................................................................
(D) 98% N2 .............................................................................................................................................................................
(E) 97% N2 .............................................................................................................................................................................
(F) No HP RPM monitoring required Datum (Average N2 at 99.5%) ...........................................................................................
(h) Installation Prohibition
After the effective date of this AD,
installation of a serviceable spare engine or
release to service of an engine after any shop
visit is allowed, provided the affected part
has not exceeded the Maximum Approved
Lives in Figures 1 or 2 to paragraph (g) of this
AD.
(i) Definition
For the purpose of this AD, a shop visit is
the induction of an engine into the shop for
maintenance or overhaul. The separation of
engine flanges solely for the purpose of
transporting the engine without subsequent
engine maintenance does not constitute an
engine shop visit.
(j) Alternative Methods of Compliance
(AMOCs)
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The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use
the procedures found in 14 CFR 39.19 to
make your request. You may email your
request to: ANE-AD-AMOC@faa.gov.
(k) Related Information
(1) For more information about this AD,
contact Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7754; fax: 781–238–7199; email:
robert.green@faa.gov.
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17:49 May 25, 2017
Jkt 241001
(2) Refer to MCAI European Aviation
Safety Agency (EASA), AD 2017–0014, dated
January 30, 2017, for more information. You
may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov by
searching for and locating it in Docket No.
FAA–2017–0186.
(3) RRD Alert Non-Modification Service
Bulletin Sp72–A1071, Revision 1, dated
January 27, 2017, which is not incorporated
by reference in this AD, can be obtained from
RRD, using the contact information in
paragraph (k)(4) of this AD.
(4) For RRD service information identified
in this AD, contact Rolls-Royce Deutschland
Ltd & Co KG, Eschenweg 11–15827
Dahlewitz, Blankenfelde-Mahlow, Germany;
phone: +49 0 33–7086–1944; fax: +49 0 33–
7086–3276.
(5) You may view this service information
at FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call 781–238–7125.
Issued in Burlington, Massachusetts, on
May 9, 2017.
Robert J. Ganley,
Acting Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10437 Filed 5–25–17; 8:45 am]
BILLING CODE 4910–13–P
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13,800
15,600
17,600
19,700
22,100
17,300
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0451; Directorate
Identifier 2017–CE–015–AD; Amendment
39–18885; AD 2017–10–11]
RIN 2120–AA64
Airworthiness Directives; Stemme AG
Gliders
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Stemme
AG Model S10–VT gliders (type
certificate previously held by Stemme
GmbH & Co. KG). This AD results from
mandatory continuing airworthiness
information (MCAI) issued by the
aviation authority of another country to
identify and correct an unsafe condition
on an aviation product. The MCAI
describes the unsafe condition as certain
propeller front transmission gear wheels
having insufficient material strength
because of improper heat treatment
SUMMARY:
E:\FR\FM\26MYR1.SGM
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]]>Agencies
[Federal Register Volume 82, Number 101 (Friday, May 26, 2017)]
[Rules and Regulations]
[Pages 24236-24239]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10437]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0186; Directorate Identifier 2017-NE-07-AD;
Amendment 39-18899; AD 2017-10-25]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 24237]]
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Rolls-Royce Deutschland Ltd & Co KG (RRD) model Spey 506-14A, Spey 555-
15, Spey 555-15H, Spey 555-15N, and Spey 555-15P turbofan engines. This
AD requires reducing the maximum approved life limits for certain high-
pressure compressor (HPC) stage 12 rotor disks. We are issuing this AD
to correct the unsafe condition on these products.
DATES: This AD becomes effective June 12, 2017.
We must receive comments on this AD by July 10, 2017.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Mail: U.S. Department of Transportation, 1200 New Jersey
Avenue SE., West Building Ground Floor, Room W12-140, Washington, DC
20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: 202-493-2251.
For service information identified in this AD, contact Rolls-Royce
Deutschland Ltd & Co KG, Eschenweg 11-15827 Dahlewitz, Blankenfelde-
Mahlow, Germany; phone: +49 0 33-7086-1944; fax: +49 0 33-7086-3276.
You may view this service information at the FAA, Engine & Propeller
Directorate, 1200 District Avenue, Burlington, MA 01803. For
information on the availability of this material at the FAA, call 781-
238-7125.
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-2017-
0186; or in person at the Docket Operations office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the mandatory continuing airworthiness information
(MCAI), regulatory evaluation, any comments received, and other
information. The address for the Docket Office (phone: 800-647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA 01803; phone: 781-238-7754; fax: 781-
238-7199; email: robert.green@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2017-0186; Directorate
Identifier 2017-NE-07-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD 2017-0014, dated January 30, 2017 (referred to hereinafter as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
Based on revised stress analysis and life calculation, Rolls-
Royce Deutschland (RRD) determined new provisional life limits for
high pressure compressor (HPC) stage 12 rotor disks, Part Number (P/
N) EU25917, P/N EU56963, P/N JR10242 and P/N JR18449, reducing the
maximum approved life limits currently defined in the RRD Spey 555-
15 Engine Maintenance Manual (EMM), Chapter 5-10-1, currently at the
revision dated July 2015 and the Engine Overhaul Manual (EOM),
Chapter 5-10, revision dated November 2014. The Spey 506-14A EMM,
Chapter 5-10-1 revision dated October 1993 as well as the Spey 506-
14A EOM, Chapter 5-10 revision dated November 1992 already contain
the applicable life limit. Failure to replace an affected HPC stage
12 rotor disk before exceeding these limits, could lead to an
uncontained engine failure, possibly resulting in damage to, and/or
reduced control of, the aeroplane. To address this potential unsafe
condition, RRD issued Alert Non-Modification Service Bulletin (NMSB)
Sp72-A1071 to provide instructions to determine (re-calculate) the
consumed and remaining service life for each part. For the reasons
described above, this AD requires re-calculation of the service life
(consumed and remaining) of the affected HPC stage 12 rotor disks
and, depending on the results, implementation of the life limits. It
is expected that the affected reduced life limits are introduced
into a next revision of the RRD Spey 555-15 Engine EMM and EOM.
You may obtain further information by examining the MCAI in the AD
docket on the Internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2017-0186.
Related Service Information
RRD has issued Alert Non-Modification Service Bulletin (NMSB) Sp72-
A1071, Revision 1, dated January 27, 2017. The Alert NMSB provides
instructions to re-calculate the consumed and remaining service life
for HPC stage 12 rotor disks, part number (P/N) EU25917, P/N EU56963,
P/N JR10242, and P/N JR18449. This service information is available by
the means identified in the ADDRESSES section.
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of
Germany, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the European Community, EASA has
notified us of the unsafe condition described in the MCAI. We are
issuing this AD because we evaluated all information provided by EASA
and determined the unsafe condition exists and is likely to exist or
develop on other products of the same type design. This AD requires
reducing the maximum approved life limits and re-calculating the
consumed and remaining service life for HPC stage 12 rotor disks P/N
EU25917, P/N EU56963, P/N JR10242, and P/N JR18449.
FAA's Determination of the Effective Date
No domestic operators use this product. Therefore, we find that
notice and opportunity for prior public comment are unnecessary and
that good cause exists for making this amendment effective in less than
30 days.
Costs of Compliance
We estimate that this AD affects 0 engines installed on airplanes
of U.S. registry. We estimate the following costs to comply with this
AD:
[[Page 24238]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Pro-rated lost life............... 1 work-hour x $85 per $3,900 $3,985 $0
hour = $85.
----------------------------------------------------------------------------------------------------------------
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.
We are 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
We 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 power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2017-10-25 Rolls-Royce Deutschland Ltd & Co KG: Amendment 39-18899;
Docket No. FAA-2017-0186; Directorate Identifier 2017-NE-07-AD.
(a) Effective Date
This AD is effective June 12, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD)
Spey 506-14A, Spey 555-15, Spey 555-15H, Spey 555-15N, and Spey 555-
15P turbofan engines with high-pressure compressor (HPC) stage 12
rotor disks, part number (P/N) EU25917, P/N EU56963, P/N JR10242, or
P/N JR18449, installed.
(d) Subject
Joint Aircraft System Component (JASC) 7230, Turbine Engine
Compressor Section.
(e) Reason
This AD was prompted by RRD re-calculating the life limits for
HPC stage 12 rotor disks, P/N EU25917, P/N EU56963, P/N JR10242, and
P/N JR18449. We are issuing this AD to prevent failure of the HPC
stage 12 rotor disk, uncontained HPC stage 12 rotor disk release,
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) Within 30 days after the effective date of this AD,
determine if:
(i) The affected part was ever operated in a Spey 555-15, Spey
555-15H, Spey 555-15N, or Spey 555-15P engine model, or
(ii) the affected part was operated soley in a Spey 506-14A
engine.
(2) If the affected part was operated solely in a Spey 506-14A
engine with no history of operating in a Spey 555-15, Spey 555-15H,
Spey 555-15N, or Spey 555-15P engine, no further action is required.
(3) If the affected part was operated in in both Spey 506-14A
and Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engine
models, or solely in Spey 555-15, Spey 555-15H, Spey 555-15N, or
Spey 555-15P engines, re-calculate the consumed cyclic life (and
remaining service life) using the Maximum Approved Life for each
engine model and take-off monitoring procedure as defined in Figures
1 and 2 to paragraph (g) of this AD.
(4) After the effective date of this AD, the Maximum Approved
Lives for the affected parts are as defined in Figure 2 to paragraph
(g) of this AD. Calculate the consumed cyclic life (and remaining
service life) using the Spey 555-15, Spey 555-15H, Spey 555-15N, or
Spey 555-15P Maximum Approved Lives in Figure 2 to paragraph (g) of
this AD.
(5) For Spey 506-14A engines with an affected part installed,
that do not have an engine shop visit after the effective date of
this AD before the re-calculated consumed cyclic life of the
affected part exceeds 14,700 flight cycles (FC), remove the affected
part from service before the re-calculated consumed cyclic life
exceeds 14,700 FC, or 50 FC or 30 days after the effective date of
this AD, whichever occurs later.
(6) For Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P
engines with an affected part installed, that do not have an engine
shop visit after the effective date of this AD before the re-
calculated consumed cyclic life of the affected part exceeds the
Maximum Approved Lives in Figure 2 to paragraph (g) of this AD,
remove the affected part from service before the re-calculated
consumed cyclic life exceeds the later of the following:
(i) Maximum Approved Lives in Figure 2 to paragraph (g) of this
AD, or
(ii) 200 FC or 90 days after the effective date of this AD, or
before exceeding the In-Service Replacement Limits defined in Figure
3 to paragraph (g) of this AD, whichever occurs first.
[[Page 24239]]
Figure 1 to Paragraph (g)--Spey 506-14A High-Pressure Compressor (HPC)
Stage 12 Rotor Disk Maximum Approved Life
------------------------------------------------------------------------
Flight cycles
------------------------------------------------------------------------
HPC stage 12 rotor disk, P/N EU25917, EU56963, and 14,700
JR10242.............................................
------------------------------------------------------------------------
Figure 2 to Paragraph (g)--Spey 555-15, Spey 555-15H, Spey 555-15N, or
Spey 555-15P HPC Stage 12 Rotor Disk, P/N EU25917, EU56963, JR10242, and
JR18449, Maximum Approved Life
------------------------------------------------------------------------
Maximum approved
Take-off monitoring procedure lives (flight
cycles)
------------------------------------------------------------------------
(A) With no high-pressure (HP) revolutions per minute 11,500
(RPM) monitoring....................................
HP RPM monitoring; stated RPM not exceeded on more
than 15% of occasions:
(B) 100% N2...................................... 13,600
(C) 99% N2....................................... 17,100
(D) 98% N2....................................... 19,300
(E) 97% N2....................................... 20,500
(F) No HP RPM monitoring required Datum (Average N2 16,800
at 99.5%)...........................................
------------------------------------------------------------------------
Figure 3 to Paragraph (g)--Spey 555-15, Spey 555-15H, Spey 555-15N, or
Spey 555-15P HPC Stage 12 Rotor Disk, P/N EU25917, EU56963, JR10242, and
JR18449, In-Service Replacement Limits
------------------------------------------------------------------------
In-service
replacement
Take-off monitoring procedure limits (flight
cycles)
------------------------------------------------------------------------
(A) With no HP RPM monitoring........................ 13,800
HP RPM monitoring; stated RPM not exceeded on more
than 15% of occasions:
(B) 100% N2...................................... 15,600
(C) 99% N2....................................... 17,600
(D) 98% N2....................................... 19,700
(E) 97% N2....................................... 22,100
(F) No HP RPM monitoring required Datum (Average N2 17,300
at 99.5%)...........................................
------------------------------------------------------------------------
(h) Installation Prohibition
After the effective date of this AD, installation of a
serviceable spare engine or release to service of an engine after
any shop visit is allowed, provided the affected part has not
exceeded the Maximum Approved Lives in Figures 1 or 2 to paragraph
(g) of this AD.
(i) Definition
For the purpose of this AD, a shop visit is the induction of an
engine into the shop for maintenance or overhaul. The separation of
engine flanges solely for the purpose of transporting the engine
without subsequent engine maintenance does not constitute an engine
shop visit.
(j) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures found in 14 CFR 39.19 to make your
request. You may email your request to: ANE-AD-AMOC@faa.gov.
(k) Related Information
(1) For more information about this AD, contact Robert Green,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803;
phone: 781-238-7754; fax: 781-238-7199; email: robert.green@faa.gov.
(2) Refer to MCAI European Aviation Safety Agency (EASA), AD
2017-0014, dated January 30, 2017, for more information. You may
examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No.
FAA-2017-0186.
(3) RRD Alert Non-Modification Service Bulletin Sp72-A1071,
Revision 1, dated January 27, 2017, which is not incorporated by
reference in this AD, can be obtained from RRD, using the contact
information in paragraph (k)(4) of this AD.
(4) For RRD service information identified in this AD, contact
Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11-15827 Dahlewitz,
Blankenfelde-Mahlow, Germany; phone: +49 0 33-7086-1944; fax: +49 0
33-7086-3276.
(5) You may view this service information at FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803.
For information on the availability of this material at the FAA,
call 781-238-7125.
Issued in Burlington, Massachusetts, on May 9, 2017.
Robert J. Ganley,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10437 Filed 5-25-17; 8:45 am]
BILLING CODE 4910-13-P
