[Federal Register Volume 82, Number 236 (Monday, December 11, 2017)]
[Rules and Regulations]
[Pages 58107-58109]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26572]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1117; Product Identifier 94-ANE-39-AD; Amendment 
39-19112; AD 2017-24-08]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding airworthiness directive (AD) 2014-24-08 for 
all Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211-
535E4-C-37 turbofan engines with certain low-pressure (LP) fuel filter-
to-high-pressure (HP) fuel pump tube assemblies, or HP fuel pump-to-
fuel flow governor (FFG) or FFG-to-HP pump inlet overspill return tube 
assemblies and flanged adaptor, installed. AD 2014-24-08 required 
replacing certain LP fuel filter-to-HP fuel pump tube assemblies. This 
AD retains the requirement in AD 2014-24-08 to remove the LP fuel 
filter-to-HP fuel pump tube, adds new compliance thresholds, and 
requires installation of new HP fuel pump-to-FFG and FFG-to-HP pump 
inlet overspill return tube assemblies and flanged adaptor. This AD was 
prompted by fuel leaks that have occurred at the flanged joints of the 
HP fuel pump-to-FFG tube assembly and FFG-to-HP pump inlet overspill 
return tube assembly. We are issuing this AD to correct the unsafe 
condition on these products.

DATES: This AD is effective January 16, 2018.

ADDRESSES: For service information identified in this final rule, 
contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936; 
email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: 
https://customers.rolls-royce.com/public/rollsroycecare. You may view 
this service information at the FAA, Engine and Propeller Standards 
Branch, 1200 District Avenue, Burlington, MA. For information on the 
availability of this material at the FAA, call 781-238-7125. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-1117.

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-2017-
1117; 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 Document 
Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7754; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2014-24-08, Amendment 39-18041 (79 FR 71308, 
December 2, 2014), ``AD 2014-24-08,'' for all RB211-535E4-37, RB211-
535E4-B-37, and RB211-535E4-C-37 turbofan engines. AD 2014-24-08 
applied to the specified products. The NPRM published in the Federal 
Register on May 26, 2017 (82 FR 24262). The NPRM proposed to continue 
to require replacing certain LP fuel filter-to-HP fuel pump tube 
assemblies. That NPRM also proposed to require installation of new HP 
fuel pump-to-FFG and FFG-to-HP pump inlet overspill return tube 
assemblies and flanged adaptor.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request To Change Installation Prohibition

    American Airlines (AAL) and FedEx Express stated the proposed AD 
would prohibit reinstallation of earlier HP fuel pump to FFG and FFG to 
HP pump inlet overspill return tube assemblies. AAL and FedEx Express 
request clarification that the HP fuel tube does not require 
replacement if removed simply to gain access to other components.
    FedEx is concerned that the current wording would result in 
serviceable tube assemblies having to be replaced in a line environment 
when components such as the FFG or fuel pump are replaced as part of 
fuel system troubleshooting. AAL didn't justify their request.
    We agree. This AD requires replacement of the affected parts before 
they exceed 4,750 engine flight cycles (FC) or 15,000 flight hours 
(FH), or at a shop visit, whichever occurs first. To address this 
comment, we deleted the Installations Prohibition paragraph and 
integrated the previous restrictions into paragraph (h), Definitions, 
adding the statement that ``The reinstallation of affected parts, 
removed to facilitate on-wing/in-service maintenance of adjacent 
components, is acceptable within the limits prescribed by paragraphs 
(g)(1) and (2) of this AD.''

Request To Change Applicability

    AAL and UPS requested clarification of shop visit. They would like 
to clarify the shop visit definition as, ``For the purpose of this AD, 
a shop visit is defined as the separation of major mating module 
flanges to perform maintenance or overhaul, excluding the removal or 
replacement of the high speed gearbox, or for the sole purpose of 
transporting the engine without performing subsequent maintenance or 
overhaul.'' They gave no justification for the requested change.

[[Page 58108]]

    We disagree. The shop visit definition is intended to require the 
replacement of parts when the engine is in a shop for maintenance or 
overhaul with no exceptions, consistent with the associated service 
bulletin. We did not change this AD.

Request To Add Credit for Previous Actions

    UPS stated the proposed AD requires incorporation of Service 
Bulletins (SBs) RB.211-73-H131, Revision 1 and RB.211-73-G230, Revision 
3. UPS requests this AD give credit for previous incorporation of any 
prior revision of these two service bulletins.
    We agree. Corrective action done prior to the effective date of 
this AD using earlier revisions of the cited service bulletins is 
acceptable. We added a new section Credit for Previous Actions after 
paragraph (h) of this AD.

Request To Change Required Actions

    UPS requested that the pre-SB RB.211-73-H131 part numbers be listed 
in paragraph (g)(1) of this AD, to clarify only pre-SB RB.73-H131 
engines are affected.
    We agree. We revised paragraph (g)(1) of this AD.

Request To Change Compliance Time

    UPS stated the proposed AD section (g)(1) requires incorporation of 
SB RB.211-73-H131 before the LP fuel filter-to-HP fuel pump tube 
exceeds 4,750 FC or 15,000 FH. These time and cycle limits appear to 
have originated with SB RB.211-73-E355, which UPS has previously 
interpreted as ``soft limits'' rather than ``hard limits'' due to the 
verbiage used in the SB. UPS requests the final rule include a drawdown 
period of 400 cycles/800 hours to allow time for operators to 
incorporate these modifications on those engines which already exceed 
the stated thresholds. UPS justified the request to prevent operational 
disruptions. RR has reviewed the original technical justification for 
introducing the life limits and modifications. Given the lives of the 
UPS fleet, a 400 flight cycle extension does not have an appreciable 
effect on engine safety. The dual engine in-flight shut down rate 
remains below the continued airworthiness threshold.
    We agree. A RR review supports the requested drawdown plan. We 
revised paragraph (g)(1) of this AD.

Request To Define Engine Hours/Cycles Since New

    UPS requests that the compliance thresholds be listed as (engine or 
part) hours/cycles since new or since last accomplishment of SB RB.211-
73-E355, whichever is sooner. They state that SB RB.211-73-E355 
installs a new LP fuel filter-to-HP fuel pump tube.
    We partially agree. We agree that time since accomplishing SB 
RB.211-73-E355 is equivalent to time since new for the replaced part. 
We disagree that the compliance thresholds need to be changed as this 
AD already specifies compliance before ``the part exceeds 4,750 engine 
flight cycles (FC) or 15,000 flight hours (FH), since new''. We did not 
change this AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Rolls-Royce plc has issued SB RB.211-73-G230, Revision 3, dated 
April 8, 2016. The SB describes a modification (mod 73-G230) and 
introduces new HP fuel pump-to-FFG and FFG-to-HP pump inlet overspill 
return tube assemblies with a larger O-ring groove on the end adaptor 
sealing face. RR has also issued SB RB.211-73-H131, Revision 1, dated 
September 2, 2014. The SB introduces a new LP fuel filter-to-HP fuel 
pump tube 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.

Costs of Compliance

    We estimate that this AD affects 100 engines installed on airplanes 
of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
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                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
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Replacement of fuel tube assemblies...  8.5 work-hours x $85 per      $17,800.00      $18,522.50   $1,852,250.00
                                         hour = $722.50.
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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.
    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

    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),

[[Page 58109]]

    (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) 
2014-24-08, Amendment 39 18041 (79 FR 71308, December 2, 2014), and 
adding the following new AD:

2017-24-08 Rolls-Royce plc: Docket No. FAA 2017-1117; Amendment 39-
19112; Product Identifier 94-ANE-39-AD.

(a) Effective Date

    This AD is effective January 16, 2018.

(b) Affected ADs

    This AD supersedes AD 2014-24-08, Amendment 39-18041 (79 FR 
71308, December 2, 2014).

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211-535E4-37, 
RB211-535E4-B-37, and RB211-535E4-C-37 turbofan engines with low-
pressure (LP) fuel filter-to-high-pressure (HP) fuel pump tube 
assembly, part number (P/N) UL16692, AE709623-1, 163521538, or 
163521545, installed; or HP fuel pump-to-fuel flow governor (FFG), 
P/N UL16691 or UL37214, installed; or FFG-to-HP pump inlet overspill 
return tube assemblies, P/N UL16690 or UL37213, installed; or 
flanged adaptor, P/N UL37218, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7321, Fuel Control/
Turbine Engines.

(e) Unsafe Condition

    This AD was prompted by reports of fuel leaks that have resulted 
in engine in-flight shutdowns. We are issuing this AD to prevent 
loss of fuel supply to the engine, which could lead to the in-flight 
shutdown of one or more engines, loss of thrust control, and damage 
to the airplane.

(f) Compliance

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

(g) Required Actions

    (1) Remove LP fuel filter-to-HP fuel pump tube assembly, P/N 
UL16692, AE709623-1, 163521538, and 163521545, and replace with a 
part eligible for installation, at the applicable compliance times 
specified in paragraphs (g)(1)(i) or (ii) of this AD, whichever 
occurs first, using the Accomplishment Instructions of RR Service 
Bulletin (SB) RB.211-73-H131, Revision 1, dated September 2, 2014.
    (i) At the next shop visit after the effective date of this AD, 
or
    (ii) at the later of the following:
    (A) Before the part exceeds 4,750 engine flight cycles (FC) or 
15,000 flight hours (FH), since new, whichever occurs first, or
    (B) Within 400 FC or 800 FH, whichever occurs first, after the 
effective date of this AD.
    (2) For affected engines with an HP fuel pump-to-FFG tube 
assembly or FFG-to-HP pump inlet overspill return tube assembly, or 
flanged adaptor, installed, replace the parts concurrent with the 
actions specified in paragraph (g)(1) of this AD, if applicable, or 
during the next shop visit, using the Accomplishment Instructions of 
RR SB RB.211-73-G230, Revision 3, dated April 8, 2016.

(h) Definitions

    (1) For the purpose of this AD, a part eligible for installation 
excludes the following: LP fuel filter-to-HP fuel pump tube 
assembly, P/N UL16692, AE709623-1, 163521538, or 163521545; HP fuel 
pump-to-FFG tube assembly, P/N UL16691 or UL37214; or FFG-to-HP pump 
inlet overspill return tube assembly, P/N UL16690 or UL37213; or 
flanged adaptor, P/N UL37218. The reinstallation of affected parts, 
removed to facilitate on-wing/in-service maintenance of adjacent 
components is acceptable within the limits prescribed by paragraphs 
(g)(1) and (2) of this AD.
    (2) For the purpose of this AD, a shop visit is the induction of 
an engine into the shop for maintenance or overhaul.

(i) Credit for Previous Actions

    You may take credit for the corrective action required by 
paragraphs (g)(1) and (2) of this AD, if you performed these actions 
before the effective date of this AD using RR Alert NMSB RB.211-73-
H131, original issue, dated May 10, 2013 or RR Alert NMSB RB.211-73-
G230, Revision 2, dated December 20, 2012, respectively.

(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 
ECO Branch, send it to the attention of the person identified in 
paragraph (l)(1) 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.

(k) Related Information

    (1) For more information about this AD, contact Robert Green, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email: 
[email protected].
    (2) Refer to MCAI European Aviation Safety Agency (EASA) AD 
2017-0006, dated January 10, 2017, and EASA AD 2014-0123, dated May 
15, 2014, for more information. You may examine the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating it in Docket No. FAA-2017-1117.

(l) 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 (SB) RB.211-73-H131, 
Revision 1, dated September 2, 2014.
    (ii) RR SB RB.211-73-G230, Revision 3, dated April 8, 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-
249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; 
Internet: https://customers.rolls-royce.com/public/rollsroycecare.
    (4) You may view this service information at FAA, Engine and 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA. 
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: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on November 22, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-26572 Filed 12-8-17; 8:45 am]
BILLING CODE 4910-13-P