AD 2017-01-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Rolls-Royce | plc | Airworthiness Directives; Rolls-Royce plc Turbofan Engines |
Unsafe Condition
Failure of the tail bearing housing (TBH) may not retain full limit load capability in all fail-safe conditions, potentially resulting in damage to the engine and the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Modify the inspection schedule for the low-pressure turbine (LPT) exhaust case and support assembly or TBH. Add an optional terminating action.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the specified inspection intervals as modified by this AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Rolls-Royce plc RB211-Trent 970-84, RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211-Trent 977B-84, and RB211-Trent 980-84 turbofan engines.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
We are superseding airworthiness directive (AD) 2014-05-25 for all Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211- Trent 977B-84, and RB211-Trent 980-84 turbofan engines. AD 2014-05-25 required inspections of the low-pressure turbine (LPT) exhaust case and support assembly or tail bearing housing (TBH) to detect cracks or damage. This AD modifies the inspection schedule for the affected engines and adds an optional terminating action. This AD was prompted by RR performing additional analysis of inspection results and determining that the existing inspections need to be modified. We are issuing this AD to correct the unsafe condition on these products.
Applicability Source Text
Show captured applicability text from the source AD
(c) Applicability
This AD applies to all Rolls-Royce plc (RR) RB211-Trent 970-84,
RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84,
[[Page 3148]]
RB211-Trent 977-84, RB211-Trent 977B-84, and RB211-Trent 980-84
turbofan engines.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 82, Number 7 (Wednesday, January 11, 2017)]
[Rules and Regulations]
[Pages 3146-3149]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-00398]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-1015; Directorate Identifier 2013-NE-37-AD;
Amendment 39-18768; AD 2017-01-01]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding airworthiness directive (AD) 2014-05-25 for
all Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84,
RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211-
Trent 977B-84, and RB211-Trent 980-84 turbofan engines. AD 2014-05-25
required inspections of the low-pressure turbine (LPT) exhaust case and
support assembly or tail bearing housing (TBH) to detect cracks or
damage. This AD modifies the inspection schedule for the affected
engines and adds an optional terminating action. This AD was prompted
by RR performing additional analysis of inspection results and
determining that the existing inspections need to be modified. We are
issuing this AD to correct the unsafe condition on these products.
DATES: This AD is effective January 26, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 26,
2017.
We must receive any comments on this AD by February 27, 2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> 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.
<bullet> Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Rolls-Royce
plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ;
phone: 011-44-1332-242424; fax: 011-44-1332-245418, or email: <a href="http://www.rolls-royce.com/contact/civil_team.jsp">http://www.rolls-royce.com/contact/civil_team.jsp</a>. 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. It is also available on
the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and
locating Docket No. FAA-2013-1015.
Examining the AD Docket
You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2013-
1015; or in person at the Docket Management Facility 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,
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: <a href="/cdn-cgi/l/email-protection#ea9885888f989ec48d988f8f84aa8c8b8bc48d859c"><span class="__cf_email__" data-cfemail="1e6c717c7b6c6a30796c7b7b705e787f7f30797168">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2013-1015; Directorate Identifier 2013-NE-37-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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Discussion
On February 27, 2014, we issued AD 2014-05-25, Amendment 39-17798
(79 FR 15665, March 21, 2014), ``AD 2014-05-25,'' for all RR RB211-
Trent 970-84, RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent
972B-84, RB211-Trent 977-84, RB211-Trent 977B-84, and RB211-Trent 980-
84 turbofan engines. AD 2014-05-25 required inspections of the LPT
exhaust case and support assembly or TBH to detect cracks or damage. AD
2014-05-25 resulted from an RR structural re-analysis indicating that
the TBH may not retain full limit load capability in all fail-safe
conditions. We issued AD 2014-05-25 to prevent failure of the
[[Page 3147]]
TBH, resulting in damage to the engine and to the airplane.
Actions Since AD 2014-05-25 Was Issued
Since we issued AD 2014-05-25, RR has analyzed inspection results
and determined that the existing inspections need to be modified. Also
since we issued AD 2014-05-25, the European Aviation Safety Agency
(EASA) has issued AD 2016-0193, dated September 30, 2016, which
modifies the inspection schedule for the affected engines and adds an
optional terminating action.
Related Service Information Under 1 CFR Part 51
RR has issued Alert Non-Modification Service Bulletin (NMSB)
RB.211-72-AG971, Revision 2, dated May 5, 2016; Alert NMSB RB.211-72-
AH154, Revision 5, dated May 5, 2016; Alert NMSB RB.211-72-AJ101, dated
May 5, 2016; and Service Bulletin (SB) RB.211-72-J055, dated March 22,
2016. RR Alert NMSB RB.211-72-AG971 describes procedures for on-wing or
in-shop inspection of the TBH mount lug run-outs. RR Alert NMSB RB.211-
72-AH154 describes procedures for an on-wing or in-shop inspection of a
pre-mod 72-J024 TBH. RR Alert NMSB RB.211-72-AJ101 describes procedures
for on-wing or in-shop inspection of a post-mod 72-J024 TBH. RR SB
RB.211-72-J055 describes procedures for modifying the engine by
introducing a revised TBH. 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
RR has also issued Technical Variance (TV) No. 124801, Issue 2,
dated July 4, 2012; TV No. 124851, Issue 2, dated July 4, 2012;
Repeater TV No. 132043, Issue 1, dated March 25, 2013; and Repeater TV
No. 132217, Issue 5, dated May 23, 2013. RR TV No. 124801 and RR TV No.
124851 provide details on the fluorescent penetrant inspection of the
TBH mount lug run-outs. RR Repeater TV No. 132043 includes details of
the inspection of the mount lug forging LE areas. RR Repeater TV No.
132217 makes the removal and installation of the exhaust nozzle and
forward and aft exhaust plugs optional tasks.
FAA's Determination
We are issuing 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.
AD Requirements
This AD modifies the inspection schedule for the affected engines
and adds an optional terminating action.
FAA's Justification and 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:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection of the TBH........... 8 work-hours x $85 per hour = $680.............. $0 $680 per inspection cycle........... $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.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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 part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2014-05-25, Amendment 39-17798 (79 FR 15665, March 21, 2014), and
adding the following new AD:
2017-01-01 Rolls-Royce plc: Amendment 39-18768; Docket No. FAA-2013-
1015; Directorate Identifier 2013-NE-37-AD.
(a) Effective Date
This AD is effective January 26, 2017.
(b) Affected ADs
This AD replaces AD 2014-05-25, Amendment 39-17798 (79 FR 15665,
March 21, 2014).
(c) Applicability
This AD applies to all Rolls-Royce plc (RR) RB211-Trent 970-84,
RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84,
[[Page 3148]]
RB211-Trent 977-84, RB211-Trent 977B-84, and RB211-Trent 980-84
turbofan engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7200, Engine
(Turbine/Turboprop).
(e) Unsafe Condition
This AD was prompted by RR performing additional analysis of
inspection results and determining that the existing inspections
need to be modified. We are issuing this AD to prevent failure of
the tail bearing housing (TBH), resulting in damage to the engine
and to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) Within the compliance times and using the service
information specified in Table 1 to paragraph (f) of this AD,
accomplish on-wing inspections of the TBH features using the
following instructions, as applicable.
(i) If during any on-wing inspection of the TBH mount lug run-
outs done using the Accomplishment Instructions, paragraph 3.A.(1),
of RR Alert Non-Modification Service Bulletin (NMSB) RB.211-72-
AG971, Revision 2, dated May 5, 2016, any cracks less than or equal
to 2 mm in length are found, remove the engine from service within
10 flight cycles (FCs). If any cracks greater than 2 mm are found,
remove the engine from service before further flight.
(ii) If during any on-wing inspection of the TBH mount lug run-
outs done using the Accomplishment Instructions, paragraph 3.A.(2),
of RR Alert NMSB RB.211-72-AG971, Revision 2, dated May 5, 2016, any
crack indications resulting in an inspection signal with an
amplitude of 50% full screen height or more are found, remove the
engine from service before further flight.
(iii) If during any on-wing inspection of a pre-mod 72-J024 TBH,
any crack or damage is found on the TBH mount lug forging leading
edge (LE) areas, re-inspect the engine or remove the engine from
service in accordance with the Accomplishment Instructions,
paragraph 3.A.(3)(t), of RR Alert NMSB RB.211-72-AH154, Revision 5,
dated May 5, 2016.
(iv) If during any on-wing inspection of a post-mod 72-J024 TBH,
any crack is found on the TBH mount lug forging LE or cutback areas,
re-inspect the engine or remove the engine from service in
accordance with the Accomplishment Instructions, paragraph
3.A.(3)(t), of RR Alert NMSB RB.211-72-AJ101, dated May 5, 2016.
(2) Within the compliance times and using the service
information specified in Table 2 to paragraph (f) of this AD, peform
in-shop inspections of the TBH features using the following
instructions, as applicable.
(i) If during any in-shop inspection of the TBH, any crack is
found on the TBH mount lug or central male catcher run-outs, replace
the TBH with a TBH eligible for installation before the engine is
returned to service.
(ii) If during any in-shop inspection of the TBH, any crack is
found on the top core vanes, reject as unserviceable or repair the
TBH in accordance with the Accomplishment Instructions, paragraph
3.C.(1)(f), of RR Alert NMSB RB.211-72-AG971 Revision 2, dated May
5, 2016, before the engine is returned to service.
(iii) If during any in-shop inspection of a pre-mod 72-J024 TBH,
any crack or damage is found on the TBH mount lug forging LE areas,
reject as unserviceable or repair the TBH in accordance with the
Accomplishment Instructions, paragraph 3.B.(2)(u)(ii), of RR Alert
NMSB RB.211-72-AH154, Revision 5, dated May 5, 2016, or the
Accomplishment Instructions, paragraph 3.C.(1)(f), of RR Alert NMSB
RB.211-72-AG971, Revision 2, dated May 5, 2016, before the engine is
returned to service.
(iv) If during any in-shop inspection of a post-mod 72-J024 TBH,
any crack is found on the TBH mount lug forging LE or cutback areas,
repair the TBH in accordance with the Accomplishment Instructions,
paragraph 3.B.(2)(u)(ii), of RR Alert NMSB RB.211-72-AJ101, dated
May 5, 2016, or the Accomplishment Instructions, paragraph
3.C.(1)(f), of Alert NMSB RB.211-72-AG971, Revision 2, dated May 5,
2016, before the engine is returned to service.
Table 1 to Paragraph (f)--TBH On-Wing Inspections
----------------------------------------------------------------------------------------------------------------
Alternate NMSB
Applicable NMSB instructions Initial Repeat inspection
Affected TBH P/N and feature and paragragph acceptable for prior inspection interval (not to
compliance exceed)
----------------------------------------------------------------------------------------------------------------
All--Mount Lug Run-outs....... RB.211-72-AG971 In-shop: RB.211-72- Before exceeding 2,200 FCs.
Revision 2, AG971 Revision 2, 2,200 FCs since
Paragraph 3.A. Paragraph 3.B or 3.C. new.
Pre-mod 72-J024 TBH--Mount Lug RB.211-72-AH154, In-shop: RB.211-72- Before exceeding 1,000 FCs.
Forging LE Areas--for a TBH Revision 5, AH154, Revision 5, 1,000 FCs since
that has not exceeded 900 FCs Paragraph 3.A. Paragraph 3.B., or new.
since new on April 7, 2014. RB.211[dash]72-AG971
Revision 2, Paragraph
3.C.
Pre-mod 72-J024 TBH--Mount Lug RB.211-72-AH154, In-shop: RB.211-72- Within 100 FCs 1,000 FCs.
Forging LE Areas--for a TBH Revision 5, AH154, Revision 5, after April 7,
that has exceeded 900 FCs Paragraph 3.A. Paragraph 3.B., or 2014.
since new on April 7, 2014. RB.211[dash]72-AG971
Revision 2, Paragraph
3.C.
Post-mod 72-J024 TBH--Mount RB.211-72-AJ101, In-shop: RB.211-72- Before exceeding 1,000 FCs.
Lug Forging LE and Cutback Paragraph 3.A. AG971, Revison 2, 1,000 FCs since
Areas. Paragraph 3.C, or NMSB
RB.211-72-AJ101, RB.211[dash]72[d
Paragraph 3.B. ash]J024
embodiment.
----------------------------------------------------------------------------------------------------------------
Table 2 to Paragraph (f)--TBH In-Shop Inspections
----------------------------------------------------------------------------------------------------------------
Alternate NMSB
Applicable NMSB instructions Initial Repeat inspection
Affected TBH P/N and feature and paragraph acceptable for prior inspection interval (not to
compliance exceed)
----------------------------------------------------------------------------------------------------------------
All--Mount Lug Run-outs....... RB.211-72-AG971, On-wing: RB.211-72- Before exceeding 2,200 FCs.
Revision 2, AG971 Rev 2, 2,200 flight FCs
Paragraph 3. Paragraph 3.A., or In- since new.
shop: RB.211-72-AG971
Revision 2, Paragraph
3.C.
All--Top Core Vanes and RB.211-72-AG971, None.................. Before exceeding 3.800 FCs.
Central Male Catcher Revision 2, 3,800 FCs since
Run[dash]outs. Paragraph 3.C. new.
[[Page 3149]]
Pre-mod 72-J024 TBH--Mount Lug RB.211-72-AH154, On-wing: RB.211-72- Before exceeding 1,000 FCs.
Forging LE Areas--for a TBH Revision 5, AH154, Revision 5, 1,000 FCs since
which has not exceeded 900 Paragraph 3.B. Section 3.A, or In- new.
FCs since new on April 7, shop: RB.211-72-
2014. AG971, Revision 2,
Paragraph 3.C.
Pre-mod 72-J024 TBH--Mount Lug RB.211-72-AJ101, On-wing: RB.211-72- Within 100 FCs 1,000 FCs.
Forging LE Areas--for a TBH Paragraph 3.B. AH154 Rev 5, Section after the
which has exceeded 900 FCs 3.A, or In[dash]shop: effective date
since new on April 7, 2014. RB.211-72-AG971, of this AD.
Revision 2, Paragraph
3.C.
Post-mod 72-J024 TBH--Mount RB.211-72-AJ101, On-wing: RB.211-72- Before exceeding 1,000 FCs.
Lug Forging LE and Cutback Paragraph 3.B. AJ101, Section 3.A, 1,000 FCs since
Areas. or In-shop: RB.211-72- NMSB
AG971 Rev 2, RB.211[dash]72-J
Paragraph 3.C. 024 embodiment.
----------------------------------------------------------------------------------------------------------------
(g) Credit For Previous Actions
(1) If you performed inspections and corrective actions on an
engine before the effective date of this AD, in accordance with
earlier versions of RR Alert NMSB RB.211-72-AG971, Revision 2, dated
May 5, 2016, or RR Alert NMSB RB.211-72-AH154, Revision 5, dated May
5, 2016, you met the requirements of paragraph (f)(1) or (2) of this
AD, as applicable.
(2) If, on or before April 7, 2014, you performed the
inspections and corrective actions required by paragraphs (f)(1) and
(2) of this AD using RR Technical Variance (TV) No. 124801, Issue 2,
dated July 4, 2012 or earlier versions; or RR TV No. 124851, Issue
2, dated July 4, 2012 or earlier versions; you met the requirements
for a mount lug run-out inspection.
(3) If, on or before April 7, 2014, you performed the
inspections and corrective actions required by paragraphs (f)(1) and
(2) of this AD using RR Repeater TV No. 132043, Issue 1, dated March
25, 2013 or earlier versions; or using RR Repeater TV No. 132217,
Issue 5, dated May 23, 2013 or earlier versions; you met the
requirements for the mount lug forging LE inspections of this AD.
(h) Optional Terminating Action
(1) Accomplishment of corrective actions required by paragraphs
(f)(1) and (2) of this AD does not constitute terminating action for
the repetitive inspections required by this AD.
(2) Modification of an engine in accordance with the
instructions of RR SB RB.211-72-J055, dated March 22, 2016,
constitutes terminating action for the repetitive inspections
required by paragraphs (f)(1) and (2) of this AD for that engine,
provided that, following this modification, no affected TBH is
installed on that engine.
(i) 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: <a href="/cdn-cgi/l/email-protection#53121d167e12177e121e1c10133532327d343c25"><span class="__cf_email__" data-cfemail="7c3d3239513d38513d31333f3c1a1d1d521b130a">[email protected]</span></a>.
(j) 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: <a href="/cdn-cgi/l/email-protection#e3918c81869197cd849186868da3858282cd848c95"><span class="__cf_email__" data-cfemail="8cfee3eee9fef8a2ebfee9e9e2cceaededa2ebe3fa">[email protected]</span></a>.
(2) Refer to MCAI European Aviation Safety Agency AD 2016-0193,
dated September 30, 2016, for more information. You may examine the
MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>
by searching for and locating it in Docket No. FAA-2013-1015.
(3) RR TV No. 124801, Issue 2, dated July 4, 2012; RR TV No.
124851, Issue 2, dated July 4, 2012, Repeater TV No. 132043, Issue
1, dated March 25, 2013, and Repeater TV No. 132217, Issue 5, dated
May 23, 2013; which are not incorporated by reference in this AD,
can be obtained from RR using the contact information in paragraph
(k)(3) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Rolls-Royce plc (RR) Service Bulletin RB.211-72-J055, dated
March 22, 2016.
(ii) RR Alert Non-Modification Service Bulletin (NMSB) RB.211-
72-AJ101, dated May 5, 2016;
(iii) RR Alert NMSB RB.211-72-AG971, Revision 2, dated May 5,
2016; and
(iv) RR Alert NMSB RB.211-72-AH154, Revision 5, dated May 5,
2016.
(3) For RR 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-
245418, or email: <a href="http://www.rolls-royce.com/contact/civil_team.jsp">http://www.rolls-royce.com/contact/civil_team.jsp</a>.
(4) 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.
(5) You may view this service information at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
<a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued in Burlington, Massachusetts, on December 22, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2017-00398 Filed 1-10-17; 8:45 am]
BILLING CODE 4910-13-P
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Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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2018-25-01 Recurring
final ruleAirworthiness Directives; Rolls-Royce plc Turbofan Engines
Unsafe Condition: Crack findings on the IPC rotor blades and IPC shaft stage 2 dovetail posts, which could lead to rotor blade separations resulting in engine failures.
2018-15-01
final ruleAirworthiness Directives; Rolls-Royce plc Turbofan Engines
Unsafe Condition: An occurrence was reported where, following N2 vibration and multiple messages, the flight crew performed an engine in-flight shut-down (IFSD) and returned to the departure airport, landing unevent...
2018-13-07
final ruleAirworthiness Directives; Rolls-Royce plc Turbofan Engines
Unsafe Condition: Occurrences were reported on RR Trent 1000 `Pack B' engines, where some IPC Rotor 1 and Rotor 2 blades were found cracked. This condition, if not detected and corrected, could lead to in-flight bla...