Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines

[Federal Register Volume 85, Number 244 (Friday, December 18, 2020)]
[Rules and Regulations]
[Pages 82302-82305]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-27897]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1032; Project Identifier MCAI-2020-00856-E; 
Amendment 39-21338; AD 2020-24-08]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG 
(Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Rolls-Royce Deutschland Ltd & Co KG (Type Certificate 
Previously Held by Rolls-Royce plc) (RRD) RB211 Trent 768-60, 772-60, 
772B-60 and 772C-60 model turbofan engines. This AD requires 
replacement of high-pressure turbine (HPT) blades with parts eligible 
for installation before exceeding specified flight cycles since new. 
This AD was prompted by several reports from the manufacturer that HPT 
blades on RB211 Trent 700 model turbofan engines have been subject to 
high levels of corrosion fatigue, leading to blade cracking and 
eventual release, resulting in an aborted take-off and in-flight shut-
downs. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective January 4, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 4, 
2021.
    The FAA must receive comments on this AD by February 1, 2021.

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 https://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 final rule, contact 
Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom, phone: 
+44 (0)1332 242424; website: https://www.rolls-royce.com/contact-us.aspx. You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call (781) 238-7759. It is 
also available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2020-1032.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-1032; 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 final rule, any 
comments received, and other information. The street address for the 
Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Scott Stevenson, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: (781) 238-7132; fax: (781) 238-7199; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No. 2018-0291, dated December 21, 2018 (referred to after this as 
``the MCAI''), to address the unsafe condition for the specified 
products. The MCAI states:

    HP turbine blades on a number of Trent 700 engines have been 
subject to high levels of corrosion fatigue, leading to blade 
cracking and eventual release. This has caused a

[[Page 82303]]

number of aborted take-off and in-flight shut-down events. Sampling 
has identified that corrosion fatigue affects blades at varying 
rates, likely dependent on environmental, operational and individual 
blade conditions.
    This condition, if not corrected, could lead to blade failure 
and subsequent increased risk of high energy debris release, 
possibly resulting in damage to, and reduced control of, the 
aeroplane.
    To address this potential unsafe condition, RR issued the NMSB 
to provide instructions for removal from service of certain engines 
where a higher level of corrosion exposure is expected for the 
affected blades.
    For the reason described above, this [EASA] AD requires removal 
from service of certain engines, to be corrected in shop.

    You may obtain further information by examining the MCAI in the AD 
docket at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2020-1032.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Rolls-Royce RB211 Trent 700 Series Alert Non-
Modification Service Bulletin (NMSB) RB.211-72-AK165, dated November 
26, 2018. The Alert NMSB describes procedures for removal of specific 
engines, identified by serial number, to enable replacement of 
potentially corrosion-fatigued HPT blades. The FAA also reviewed Task 
72-41-52-200-800--General Data for the Inspection of the High Pressure 
(HP) Turbine Blades, dated June 10, 2011, from the (Rolls-Royce) RR 
Trent-768-60/15 Engine Manual. This Task describes procedures for 
inspection of the HPT 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 
ADDRESSES.

FAA's Determination

    This product has been approved by EASA 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 and service information referenced 
above. The FAA is issuing this AD because it evaluated all the relevant 
information provided by EASA and determined that the unsafe condition 
described previously is likely to exist or develop in other products of 
the same type design.

AD Requirements

    This AD requires replacement of HPT blades on affected engines 
prior to accumulating a specified number of flight cycles since new, or 
before further flight, whichever occurs later.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C.) authorizes agencies to dispense with notice and comment 
procedures for rules when the agency, for ``good cause,'' finds that 
those procedures are ``impracticable, unnecessary, or contrary to the 
public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than 30 days, upon 
a finding of good cause.
    The FAA has found the risk to the flying public justifies waiving 
notice and comment prior to adoption of this rule because no domestic 
operators use this product. It is unlikely that the FAA will receive 
any adverse comments or useful information about this AD from U.S. 
operators. Accordingly, notice and opportunity for prior public comment 
are unnecessary, pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for 
the foregoing reasons, the FAA finds that good cause exists pursuant to 
5 U.S.C. 553(d) for making this amendment effective in less than 30 
days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, the FAA invites you to send any written data, views, 
or arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the FAA-2020-1032 and 
Project Identifier MCAI-2020-00856-E at the beginning of your comments. 
The most helpful comments reference a specific portion of the proposal, 
explain the reason for any recommended change, and include supporting 
data. The FAA will consider all comments received by the closing date 
and may amend this final rule because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The FAA will also post a report summarizing each substantive 
verbal contact received about this final rule.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this final rule contain 
commercial or financial information that is customarily treated as 
private, that you actually treat as private, and that is relevant or 
responsive to this final rule, it is important that you clearly 
designate the submitted comments as CBI. Please mark each page of your 
submission containing CBI as ``PROPIN.'' The FAA will treat such marked 
submissions as confidential under the FOIA, and they will not be placed 
in the public docket of this final rule. Submissions containing CBI 
should be sent to Scott Stevenson, Aviation Safety Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803. Any commentary 
that the FAA receives which is not specifically designated as CBI will 
be placed in the public docket for this rulemaking.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 0 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Remove and replace HPT blades.......  52 work hours x $85 per      $1,500,000       $1,504,420               $0
                                       hour = $4,420.
----------------------------------------------------------------------------------------------------------------


[[Page 82304]]

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation Programs'' 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

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, and
    (2) Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

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):

2020-24-08 Rolls-Royce Deutschland Ltd & Co KG (Type Certificate 
Previously Held by Rolls-Royce plc): Amendment 39-21338; Docket No. 
FAA-2020-1032; Project Identifier MCAI-2020-00856-E.

(a) Effective Date

    This AD is effective January 4, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce Deutschland Ltd & Co KG (Type 
Certificate Previously Held by Rolls-Royce plc) (RRD) RB211 Trent 
768-60, 772-60, 772B-60, and 772C-60 model turbofan engines with an 
engine serial number (ESN) identified in Table 1 or Table 2 of 
Appendix 1 of Rolls-Royce (RR) RB211 Trent 700 Series Alert Non-
Modification Service Bulletin RB.211-72-AK165, dated November 26, 
2018 (the NMSB).

(d) Subject

    Joint Aircraft System Component (JASC) Code/Air Transport 
Association (ATA) of America Code 7250--Turbine Section.

(e) Unsafe Condition

    This AD was prompted by a determination by the manufacturer that 
high-pressure turbine (HPT) blades on several RB211 Trent 700 model 
turbofan engines have been subject to high levels of corrosion 
fatigue, leading to HPT blade cracking and eventual release. The FAA 
is issuing this AD to prevent failure of the HPT blades. The unsafe 
condition, if not addressed, could result in blade failure and 
subsequent release of high-energy debris, possibly resulting in 
damage to, and reduced control of, the airplane.

(f) Compliance

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

(g) Required Actions

    (1) For engines with an ESN listed in Table 1 of Appendix 1 of 
the NMSB, prior to each HPT blade accumulating 3,500 flight cycles 
since new, or before further flight after the effective date of this 
AD, whichever occurs later, remove the HPT blade from service and 
replace with a part eligible for installation.
    (2) For engines with an ESN listed in Table 2 of Appendix 1 of 
the NMSB, prior to each HPT blade accumulating 5,800 flight cycles 
since new, or before further flight after the effective date of this 
AD, whichever occurs later, remove the HPT blade from service and 
replace with a part eligible for installation.
    (3) If the flight cycles since new of an HPT blade are unable to 
be determined, use the flight cycles since new, flight cycles since 
refurbishment, or flight cycles since overhaul of the HPT module.

(h) Definition

    For the purpose of this AD, ``a part eligible for installation'' 
is:
    (1) An HPT blade that has:
    (i) Been removed from an engine with a serial number listed in 
Table 1 of the NMSB; and
    (ii) not exceeded 3,500 flight cycles since new; and
    (iii) before installation, passed an inspection (no crack 
detected) in accordance with Task 72-41-52-200-800--General Data for 
the Inspection of the High Pressure (HP) Turbine Blades, dated June 
10, 2011, from the (Rolls-Royce) RR Trent-768-60/15 Engine Manual 
(RR Task 72-41-52-200-800); or
    (2) An HPT blade that has:
    (i) Been removed from an engine with a serial number listed in 
Table 2 of the NMSB; and
    (ii) not exceeded 5,800 flight cycles since new; and
    (iii) before installation, passed an inspection (no crack 
detected) in accordance with Task 72-41-52-200-800--General Data for 
the Inspection of the High Pressure (HP) Turbine Blades, dated June 
10, 2011, from the RR Trent-768-60/15 Engine Manual (RR Task 72-41-
52-200-800); or
    (3) An HPT blade with zero flight cycles since new.

(i) No Reporting Requirements

    The reporting requirements specified in paragraph R. of RR Task 
72-41-52-200-800 are not required by this AD.

(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 Related Information. 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 Scott Stevenson, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7132; fax: (781) 238-7199; 
email: [email protected].
    (2) Refer to European Aviation Safety Agency (EASA) AD No. 2018-
0291, dated December 21, 2018, for more information. You may examine 
the EASA AD in the AD docket at https://www.regulations.gov by 
searching for and locating it in Docket No. FAA-2018-1032.

(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 RB211 Trent 700 Series Alert Non-Modification 
Service Bulletin RB.211-72-AK165, dated November 26, 2018.
    (ii) Task 72-41-52-200-800--General Data for the Inspection of 
the High Pressure (HP) Turbine Blades, dated June 10, 2011, from

[[Page 82305]]

the (Rolls-Royce) RR Trent-768-60/15 Engine Manual.
    (3) For service information identified in this AD, contact 
Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom, 
phone: +44 (0)1332 242424; website: https://www.rolls-royce.com/contact-us.aspx.
    (4) You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call (781) 238-7759.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on November 17, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-27897 Filed 12-17-20; 8:45 am]
BILLING CODE 4910-13-P

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