[Federal Register Volume 83, Number 157 (Tuesday, August 14, 2018)]
[Proposed Rules]
[Pages 40161-40164]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-17405]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0538; Product Identifier 2012-NE-47-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2017-03-
02, which applies to certain Rolls-Royce plc (RR) RB211 Trent 768-60, 
772-60, and 772B-60 turbofan engines. AD 2017-03-02 requires initial 
and repetitive ultrasonic inspections (UIs) of the affected low-
pressure (LP) compressor blades. Since we issued AD 2017-03-02, RR 
issued revised service information to reduce the inspection threshold 
for UIs of the affected blades. This proposed AD would retain the UIs 
in AD 2017-03-02 while reducing the inspection threshold. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by September 28, 
2018.

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 http://www.regulations.gov. 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: 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, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011-44-1332-
242424; fax: 011-44-1332-249936, or email: http://www.rolls-royce.com/contact/civil_team.jsp. You may view this service information at the 
FAA, Engine and Propeller Standards Branch, 1200 District Avenue, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call 781-238-7759.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0538; 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 (MCAI), 
the regulatory evaluation, any comments received, and other 
information. The address for Docket Operations (phone: 800-647-5527) is 
listed above. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Kevin M. Clark, Aerospace Engineer, 
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 
781-238-7088; fax: 781-238-7199; email: <a href="/cdn-cgi/l/email-protection#167d73607f78387b38757a77647d5670777738717960"><span class="__cf_email__" data-cfemail="e38886958a8dcd8ecd808f829188a3858282cd848c95">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the

[[Page 40162]]

ADDRESSES section. Include ``Docket No. FAA-2018-0538; Product 
Identifier 2012-NE-47-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM because 
of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued AD 2017-03-02, Amendment 39-18793 (82 FR 10701, February 
15, 2017), (``AD 2017-03-02''), for certain RR RB211 Trent 768-60, 772-
60, and 772B-60 turbofan engines with LP compressor blade, part number 
(P/N) FK23411, FK25441, FK25968, FW11901, FW15393, FW23643, FW23741, 
FW23744, KH23403, or KH23404, installed. AD 2017-03-02 requires the UIs 
of the affected LP compressor blades. AD 2017-03-02 resulted from 
revised service information to reduce the inspection threshold of the 
UI for the LP compressor blades. We issued AD 2017-03-02 to correct the 
unsafe condition on these products.

Actions Since AD 2017-03-02 Was Issued

    Since we issued AD 2017-03-02, further analysis determined that the 
initial and repetitive inspection threshold described in Revision 3 of 
Rolls-Royce Alert Non-Modification Service Bulletin (NMSB) RB.211-72-
AH465 must be further reduced from 2,400 cycles to 1,200 cycles. 
Therefore, RR issued Revision 4 of Alert NMSB RB.211-72-AH465, dated 
October 3, 2017. Also, since we issued AD 2017-03-02, the European 
Aviation Safety Agency (EASA) issued AD 2017-0241, dated December 6, 
2017, which requires ultrasonic inspection of each affected LP 
compressor blade within the compliance time specified in Section 1.D. 
of RR Alert NMSB RB.211-72-AH465.

Related Service Information Under 1 CFR Part 51

    We reviewed Rolls-Royce Alert NMSB RB.211-72-AH465, Revision 4, 
dated October 3, 2017. The Alert NMSB describes procedures for 
performing initial and repetitive UI of the LP compressor blades. 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

    We also reviewed the following service information: RR NMSB RB.211-
72-G702, dated May 23, 2011; RR NMSB RB.211-72-G872, Revision 2, dated 
March 8, 2013, or earlier revisions; RR NMSB RB.211-72-H311, dated 
March 8, 2013; RR Engine Manual E-Trent-1RR, Task 72-31-11-200-806; or 
Airbus A330 Aircraft Maintenance Manual (AMM), Tasks 72-31-41-270-801 
or 72-31-41-270-802. These service documents describe the inspection 
procedures for the UI of the Trent 700 LP compressor blades.

FAA's Determination

    We are 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 all requirements of AD 2017-03-02. 
This proposed AD would reduce the inspection threshold for UI of the LP 
compressor blades from 2,400 cycles to 1,200 cycles. This proposed AD 
would also require accomplishing the actions specified in the service 
information described previously.

Differences Between the Proposed AD and the MCAI or Service Information

    The compliance time of this proposed AD differs from EASA AD 2017-
0241 in that, for blades with 2,400 cycles since new or cycles since 
last inspection on the effective date of this AD, this AD requires 
inspection within 30 days after the effective date of this AD. EASA AD 
2017-0241 specifies that all blades must be inspected before 
accumulating 2,400 cycles.

Costs of Compliance

    We estimate that this proposed AD affects 56 engines installed on 
airplanes of U.S. registry.
    We estimate 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.........................  44 work-hours x $85 per                  $0          $3,740        $209,440
                                      hour = $3,740.
----------------------------------------------------------------------------------------------------------------

    This proposed AD provides updated labor cost for completing the UI 
of the LP compressor blades as a correction to AD 2017-03-02.

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

    We have 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

[[Page 40163]]

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) 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, 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.

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) 
2017-03-02, Amendment 39-18793 (82 FR 10701, February 15, 2017), and 
adding the following new AD:

Rolls-Royce plc: Docket No. FAA-2018-0538; Product Identifier 2012-
NE-47-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by September 28, 
2018.

(b) Affected ADs

    This AD replaces AD 2017-03-02, Amendment 39-18793 (82 FR 10701, 
February 15, 2017).

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211 Trent 768-60, 772-
60, and 772B-60 turbofan engines with low-pressure (LP) compressor 
blade, part number (P/N) FK23411, FK25441, FK25968, FW11901, 
FW15393, FW23643, FW23741, FW23744, KH23403, or KH23404, installed.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by LP compressor blade partial airfoil 
release events that occurred in-service on RR Trent 700 engines. 
While released sections were contained in each case, projection of 
secondary debris and effects could present a potential hazard. We 
are issuing this AD to prevent LP compressor blade airfoil 
separation. The unsafe condition, if not addressed, could result in 
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) After the effective date of this AD, perform an ultrasonic 
inspection (UI) of each LP compressor blade within the compliance 
time specified in Figure 1 to paragraph (g) of this AD, and 
thereafter at intervals not to exceed 1,200 cycles since last 
inspection (CSLI).
    (2) Use the Accomplishment Instructions, paragraph 3, excluding 
subparagraphs 3.C.(2)(b), 3.D.(2), and 3.G.(1), of RR Alert Non-
Modification Service Bulletin (NMSB) RB.211-72-AH465, Revision 4, 
dated October 3, 2017, to perform the inspections required by this 
AD.
[GRAPHIC] [TIFF OMITTED] TP14AU18.001

    (3) If an LP compressor blade fails the inspection required by 
this AD, replace the blade with a part eligible for installation, 
prior to return to service.

(h) Parts Installation

    After the effective date of this AD, LP compressor blade, P/N 
FK23411, FK25441, FK25968, FW11901, FW15393, FW23643, FW23741, 
FW23744, KH23403, or KH23404, is eligible for installation if the LP 
compressor blade has not exceeded 1,200 CSN or CSLI.

(i) Credit for Previous Actions

    You may take credit for the UIs required by paragraph (g) of 
this AD, if you performed the UIs before the effective date of this 
AD using the following service information: RR NMSB RB.211-72-AH465, 
Revision 3, dated April 27, 2017, or earlier revisions; RR NMSB 
RB.211-72-G702, dated May 23, 2011; RR NMSB RB.211-72-G872, Revision 
2, dated March 8, 2013, or earlier revisions; RR NMSB RB.211-72-
H311, dated March 8, 2013; RR Engine Manual E-Trent-1RR, Task 72-31-
11-200-806; or Airbus A330 Aircraft Maintenance Manual (AMM), Tasks 
72-31-41-270-801 or 72-31-41-270-802.

[[Page 40164]]

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
certification office, send it to the attention of the person 
identified in paragraph (k)(1) of this AD. You may email your 
request to: <a href="/cdn-cgi/l/email-protection#73323d365e32375e323e3c30331512125d141c05"><span class="__cf_email__" data-cfemail="d4959a91f99590f995999b9794b2b5b5fab3bba2">[email protected]</span></a>.
    (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.

(k) Related Information

    (1) For more information about this AD, contact Kevin M. Clark, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7088; fax: 781-238-7199; email: 
<a href="/cdn-cgi/l/email-protection#076c62716e69296a29646b66756c4761666629606871"><span class="__cf_email__" data-cfemail="91faf4e7f8ffbffcbff2fdf0e3fad1f7f0f0bff6fee7">[email protected]</span></a>.
    (2) For service information identified in this AD, contact 
Rolls-Royce plc, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011-
44-1332-242424; fax: 011-44-1332-249936, or email: http://www.rolls-royce.com/contact/civil_team.jsp. You may 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 August 9, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-17405 Filed 8-13-18; 8:45 am]
BILLING CODE 4910-13-P


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