[Federal Register Volume 85, Number 234 (Friday, December 4, 2020)]
[Rules and Regulations]
[Pages 78215-78219]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-26730]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0425; Project Identifier 2016-NE-13-AD; Amendment
39-21346; AD 2020-25-04]
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.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2016-24-08
for all Rolls-Royce Deutschland Ltd. & Co KG (RRD) RB211-Trent 875-17,
RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-
Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 model
turbofan engines. AD 2016-24-08 required repetitive inspections of the
engine upper bifurcation nose fairing assembly and repair or
replacement of any fairing assembly that fails inspection. This AD
retains the requirements to perform repetitive inspections of the
engine upper bifurcation nose fairing assembly and repair or
replacement of any fairing assembly that fails inspection. As a
terminating action to these inspections, this AD also requires the
modification of the engine upper bifurcation nose fairing assembly. The
FAA is issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective January 8, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 8,
2021.
ADDRESSES: For service information identified in this final rule,
contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby,
England, DE24 8BJ; phone: (+44) 1332 242424; fax: (+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, 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-2019-0425.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2019-0425; 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 AD, the mandatory
continuing airworthiness information (MCAI), any comments received, and
other information. The address for Docket Operations is 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: 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:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2016-24-08, Amendment 39-18725 (81 FR
86567, December 1, 2016) (AD 2016-24-08). AD 2016-24-08 applied to all
RR RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-
Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent
895-17 model turbofan engines. The NPRM published in the Federal
Register on June 24, 2019 (84 FR 29423). The NPRM was prompted by RRD
developing a modification of the engine upper bifurcation nose fairing
assembly that terminates the need for repetitive inspections of this
part. In the NPRM, the FAA proposed to retain the requirements to
perform repetitive inspections of the engine upper bifurcation nose
fairing assembly and repair or replacement of any fairing assembly that
fails inspection. As a terminating action, in the NPRM the FAA also
proposed to require modification of the engine upper bifurcation nose
fairing assembly. The FAA is issuing this AD to address the unsafe
condition of these products.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD 2018-0088, dated April 18, 2018 (referred to after this as ``the
MCAI''), to address the unsafe condition on these products. The MCAI
states:
[[Page 78216]]
Inspection of in-service Trent 800 engines identified cracking
and/or material release from the upper bifurcation fairing, which
mates to the aeroplane thrust reverser upper bifurcation forward
fire seal. Both sets of hardware create the engine firewall to
isolate the engine compartment fire zone, which is a firewall
feature of the aeroplane type design. Damage (missing materials and
holes/openings) to the upper bifurcation fairing creates a breach of
the engine fire wall, which may decrease the effectiveness of the
engine fire detection and suppression systems due to excess fan air
entering the engine compartment fire zone. This could delay or
prevent the fire detection and suppression system from functioning
properly, and can result in an increased risk of prolonged burning,
potentially allowing a fire to reach unprotected areas of the
engine, strut and wing.
This condition, if not detected and corrected, could lead to an
uncontrolled fire, possibly resulting in damage to, or loss of, the
aeroplane.
To address this potential unsafe condition, RR published the
NMSB to provide inspection instructions. Consequently, EASA issued
AD 2016-0084 to require repetitive inspections of the upper
bifurcation fairing and, depending on findings, accomplishment of
applicable corrective action(s).
Since that [EASA] AD was issued, RR developed modification (mod)
72-J803, which introduces a revised upper bifurcation nose fairing
assembly, featuring an additional support bracket assembly at the
right hand seal land. RR also published the modification SB to
provide instructions for in-service engines. This modification
removes the need for repetitive inspections.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2016-0084, which is superseded, and requires
a modification, which constitutes terminating action for the
repetitive inspections required by this [EASA] AD.
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-2019-0425.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from six commenters. The commenters were
Rolls-Royce plc (RR); American Airlines (AAL); The Boeing Company
(Boeing); Delta Air Lines, Inc. (DAL); and two individual commenters.
Five commenters requested changes to this AD, which included adding or
updating the unsafe condition, terminating action, installation
prohibition, and credit for previous actions. One commenter requested
clarification regarding on-wing rework. One commenter expressed support
for the AD. The following presents the comments received on the NPRM
and the FAA's response to each comment.
Request To Remove Statement Indicating the Unsafe Condition Could Cause
a Fire
Boeing requested that paragraph (e), Unsafe Condition, of this AD
be revised to replace ``. . . could result in engine fire and damage to
the airplane'' with ``. . . could result in reduced ability to detect
and/or control an engine fire which could lead to damage to the
airplane.'' Boeing reasoned that unsafe condition is not expected to
cause an engine fire. Instead, when material is liberated from the
engine upper bifurcation nose fairing assembly, the core zone fire
detection and extinguishing may be less effective in the event of a
fire. This is due to airflow that may be allowed to pass into the fire
zone through an alternate path and at an unknown rate compared to the
intended design.
The FAA partially agrees. The FAA agrees that a cracked engine
upper bifurcation nose fairing assembly and material release would not
lead to an engine fire. The unsafe condition of this AD, however, is
not the cracking of the engine upper bifurcation nose fairing assembly
and material release, but the resulting failure of the engine fire
control system. Since the engine fire control system would be
inadequate to detect and control an engine fire, regardless of cause,
the resulting hazard is the engine fire and consequent damage to the
airplane. The FAA did not change this AD.
Request To Clarify Engine Upper Bifurcation Nose Fairing Assembly With
FRSJ739 Repair
DAL requested that Note 1 to paragraph (g)(3) of this AD be updated
to clarify inspection if on-wing repair FRSJ739 was applied. DAL
reasoned that RRD added a second sheet to Figure 1 when it published
Revision 2 of RR Alert Non-Modification Service Bulletin (NMSB) RB.211-
72-AJ165, on August 21, 2018. This second sheet includes the entire
length of the bracket in Zone A if on-wing repair FRSJ739 was applied.
The proposed AD did not provide any distinctions for on-wing repair
FRSJ739.
The FAA disagrees. As stated in Note 1 to paragraph (g)(3) of this
AD, Figure 1 of RR Alert NMSB RB.211-72-AJ165, Revision 2, dated August
21, 2018, provides guidance on the engine upper bifurcation nose
fairing assembly inspection locations. Operators are not required to
use Figure 1 to comply with this AD. Therefore, this AD is not required
to reference on-wing repair FRSJ739.
Request To Add Credit for Previous Actions Paragraph
DAL requested that the FAA add a Credit for Previous Actions
paragraph to this AD for previous initial and repetitive inspections
completed using RR Alert NMSB RB.211-72-AJ165, Initial Issue, dated
March 31, 2016, required by AD 2016-24-08.
The FAA disagrees. AD 2016-24-08 and this AD do not require use of
RR Alert NMSB RB.211-72-AJ165 to perform the initial and repetitive
inspections. RR Alert NMSB RB.211-72-AJ165 is provided as guidance on
engine upper bifurcation nose fairing assembly inspection locations.
Therefore, this AD does not need to provide credit for inspections
performed using RR Alert NMSB RB.211-72-AJ165. The FAA did not change
this AD.
Request To Update Terminating Action With the Latest Service
Information
AAL, Boeing, DAL, and an individual commenter requested that
paragraph (h), Mandatory Terminating Action, of this AD be updated to
include RR Service Bulletin (SB) RB.211-72-J803, Revision 2, dated
April 1, 2019. The commenters reasoned that RR SB RB.211-72-J803,
Revision 1, dated July 13, 2018, has been superseded by Revision 2,
dated April 1, 2019. Boeing also suggested adding language that allows
any later revisions of the service information to be equivalent action
as RRD may publish further revisions.
The FAA agrees to revise the reference to RR SB RB.211-72-J803 in
paragraph (h) of this AD from Revision 1, dated July 13, 2018, to
Revision 2, dated April 1, 2019. The FAA disagrees with adding language
that allows any later revisions of the service information. Since later
revisions of the service information have not been published or
reviewed by the agency, the FAA will not require their use.
With the update to RR SB RB.211-72-J803 in this AD from Revision 1,
dated July 13, 2018, to Revision 2, dated April 1, 2019, the FAA
determined the need to update the estimated costs to reflect the
increase in labor hours from 2 work-hours to 8 work-hours for both on-
wing and in-shop visits.
Request To Add On-Wing Mandatory Terminating Action
DAL requested that the on-wing rework instructions introduced in
the Accomplishment Instructions, paragraph 3.D., of RR SB RB.211-72-
J803, Revision 2, dated April 1, 2019, be included as an option for the
mandatory terminating action to the AD. DAL
[[Page 78217]]
added that paragraph (i), Installation Prohibition, will ensure that
de-modification of the engine upper bifurcation nose fairing assembly
will not be possible once the reworked engine upper bifurcation nose
fairing assembly is installed.
The FAA agrees that the on-wing rework instructions should be added
as an option to the mandatory terminating action in addition to the in-
shop rework procedure. RR SB RB.211-72-J803, Revision 2, dated April 1,
2019, provides an option to perform the on-wing rework instructions. As
a result, operators can perform the rework in-shop or on-wing. The FAA
added the on-wing rework instructions to the mandatory terminating
action section of this AD.
The FAA also agrees that de-modification of the engine upper
bifurcation nose fairing assembly will not be possible once the
reworked engine upper bifurcation nose fairing assembly is installed.
As noted in the following comment response, the FAA removed the
installation prohibition proposed in the NPRM as the mandatory
terminating actions requiring the modification of the engine upper
bifurcation nose fairing assembly makes this installation prohibition
unnecessary.
Request To Revise Installation Prohibition
RR and AAL requested that paragraph (i), Installation Prohibition,
of the proposed AD be revised. Rolls-Royce was concerned if an upper
bifurcation panel (upper bifurcation nose fairing assembly) is required
to complete an on-wing repair, it will prevent the installation of the
original panel without the part being modified to the later standard.
AAL reasoned that a serviceable engine upper bifurcation nose fairing
assembly that needs to be repaired or replaced per AD 2016-24-08, but
has not been, may be removed during non-related maintenance. The FAA
infers that RR's concern aligns with AAL reasoning that removal of a
panel for on-wing activity, such as maintenance or repair unrelated to
the rework, will make the part ineligible for installation. Therefore,
AAL proposed that paragraph (i) of the proposed AD be revised to
``After the effective date of this AD, do not install an engine upper
bifurcation nose fairing assembly, P/N FK25470, onto any engine that
has or had an engine upper bifurcation nose fairing assembly, P/N
KH75280, installed.''
The FAA agrees that the installation prohibition would prevent the
installation of the engine upper bifurcation nose fairing assembly, P/N
FK25470, onto any engine after the effective date of this AD, even for
work unrelated to this AD. The mandatory terminating action requires
the modification of engine upper bifurcation nose fairing assembly, P/N
FK25470 and, as such, the installation prohibition is not necessary.
The FAA removed the installation prohibition from this AD.
Support for the AD
An individual commenter expressed support for the AD as written.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety requires adopting the AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, and
any other changes described previously, this AD is adopted as proposed
in the NPRM. None of the changes will increase the economic burden on
any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed RR SB RB.211-72-J803, Revision 2, dated April 1,
2019; Revision 1, dated July 13, 2018; and Initial Issue, dated
December 7, 2017. The service information describes procedures for
modification of the engine upper bifurcation nose fairing 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 ADDRESSES.
Other Related Service Information
The FAA reviewed RR Alert NMSB RB.211-72-AJ165, Revision 2, dated
August 21, 2018. The NMSB provides guidance on engine upper bifurcation
nose fairing assembly inspection locations. The FAA also reviewed AMM
TASK 70-20-02, Water Washable Fluorescent Penetrant Inspection
(Maintenance Process 213), and OMat 632, high sensitivity fluorescent
penetrant inspection. This service information provides guidance on
performing a fluorescent penetrant inspection.
Costs of Compliance
The FAA estimates that this AD affects 70 engines installed on
airplanes of U.S. registry. Based on updated information since
publication of the NPRM, the FAA revised the estimated number of
engines installed on airplanes of U.S. registry from 125 in the NPRM to
70 in this final rule.
The FAA estimates 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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Inspect engine upper bifurcation nose 3.25 work-hours x $85 $0 $276.25 $19,337.50
fairing assembly. per hour = $276.25.
Modify engine upper bifurcation nose 8 work-hours x $85 per 50 730 51,100
fairing assembly. hour = $680.
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The FAA estimates the following costs to do any necessary repairs
or replacements that would be required based on the results of the
mandated inspections. The agency has no way of determining the number
of engines that might need these repairs or replacements:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Repair engine upper bifurcation nose fairing 8 work-hours x $85 per hour = $500 $1,180
assembly. $680.
[[Page 78218]]
Replace engine upper bifurcation nose fairing 30 work hours x $85 per hour = 500 3,050
assembly. $2,550.
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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.
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
The FAA has 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 that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) 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 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:
0
a. Removing airworthiness directive AD 2016-24-08, Amendment 39-18725
(81 FR 86567, December 1, 2016); and
0
b. Adding the following new airworthiness directive:
2020-25-04 Rolls-Royce Deutschland Ltd & Co KG (Type Certificate
previously held by Rolls-Royce plc): Amendment 39-21346; Docket No.
FAA-2019-0425; Project Identifier 2016-NE-13-AD.
(a) Effective Date
This airworthiness directive (AD) is effective January 8, 2021.
(b) Affected ADs
This AD replaces AD 2016-24-08, Amendment 39-18725 (81 FR 86567,
December 1, 2016).
(c) Applicability
This AD applies to all Rolls-Royce Deutschland Ltd. & Co KG
(RRD) (Type Certificate previously held by Rolls-Royce plc) RB211-
Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent
884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent
895-17 model turbofan engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7130, Engine
Fireseals.
(e) Unsafe Condition
This AD was prompted by RRD developing a modification of the
engine upper bifurcation nose fairing assembly as a result of
reports of cracking and material release from an engine upper
bifurcation fairing. The FAA is issuing this AD to prevent failure
of the engine fire control system. The unsafe condition, if not
addressed could result in engine fire and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within 7,500 engine flight hours (FHs) since new or since
the last inspection or within 150 flight cycles (FCs) after January
5, 2017 (the effective date of AD 2016-24-08), whichever occurs
later, inspect the engine upper bifurcation nose fairing assembly
for cracks or missing material. Use paragraph (g)(3) of this AD to
perform the inspection.
(2) Repeat the inspection required by paragraph (g)(1) of this
AD within every 7,500 engine FHs since the last inspection.
(3) Inspect the engine upper bifurcation nose fairing assembly
as follows.
Note 1 to Paragraph (g)(3): Figure 1 of Rolls-Royce plc (RR)
Alert Non-Modification Service Bulletin (NMSB) RB.211-72-AJ165,
Revision 2, dated August 21, 2018, provides guidance on the engine
upper bifurcation nose fairing assembly inspection locations.
(i) Visually inspect upper bifurcation fairing seal face 22,
seal support 23, and Zone A for any cracks or material loss on the
right side.
(A) If fairing seal face 22 is found to have released material,
repair or replace the fairing before further flight.
(B) If there is a single crack found on fairing seal face 22,
shorter than 6 mm, repair or replace the fairing within 100 engine
FCs, or at the next engine shop visit, whichever occurs first.
(C) If there is a single crack, longer than 6 mm, found on
fairing seal face 22, repair or replace the fairing within 15 engine
FCs or at the next engine shop visit, whichever occurs first.
(D) If there are two or more cracks found on fairing seal face
22, replace the fairing within 15 engine FCs or at the next engine
shop visit, whichever occurs first.
(E) If there is any cracking or material loss found on seal
support 23, replace the fairing within 15 engine FCs or at the next
engine shop visit, whichever occurs first.
(ii) If the visual inspection required by paragraph (g)(3)(i) of
this AD does not detect any cracks, fluorescent penetrant inspect
Zone A.
(A) If a crack shorter than 6 mm is detected, repair or replace
the fairing within 100 engine FCs, or at the next engine shop visit,
whichever occurs first.
(B) If a crack longer than 6 mm is detected, repair or replace
the fairing within 15 engine FCs or at the next engine shop visit,
whichever occurs first.
Note 2 to Paragraph (g)(3)(ii): AMM TASK 70-20-02, Water
Washable Fluorescent Penetrant Inspection (Maintenance Process 213),
and OMat 632, high sensitivity fluorescent penetrant inspection,
provides guidance on performing a fluorescent penetrant inspection.
(h) Mandatory Terminating Action
As a mandatory terminating action to the inspections of the
engine upper bifurcation nose fairing assembly required by paragraph
(g) of this AD, perform one of the following:
(1) At the next engine shop visit after the effective date of
this AD, modify the engine upper bifurcation nose fairing assembly
in
[[Page 78219]]
accordance with the Accomplishment Instructions, paragraph 3.C., of
RR Service Bulletin (SB) RB.211-72-J803, Revision 2, dated April 1,
2019; paragraph 3.B., Revision 1, dated July 13, 2018; or paragraph
3.B., Original Issue, dated December 7, 2017; or
(2) Before the next engine shop visit after the effective date
of this AD, modify the engine upper bifurcation nose fairing
assembly in accordance with the Accomplishment Instructions,
paragraph 3.D., of RR SB RB.211-72-J803, Revision 2, dated April 1,
2019.
(i) Definition
For the purpose of this AD, an ``engine shop visit'' is defined
as the induction of an engine into the shop for maintenance
involving the separation of pairs of major mating engine flanges,
except that the separation of engine flanges solely for the purposes
of transportation without subsequent engine maintenance does not
constitute an engine shop visit.
(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 2018-
0088, dated April 18, 2018, for more information. You may examine
the EASA AD in the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2019-0425.
(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.211-72-J803,
Revision 2, dated April 1, 2019.
(ii) RR SB RB.211-72-J803, Revision 1, dated July 13, 2018.
(iii) RR SB RB.211-72-J803, Initial Issue, dated December 7,
2017.
(3) For RR service information identified in this AD, contact
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby,
England, DE24 8BJ; phone: (+44) 1332 242424; fax: (+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, 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 30, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-26730 Filed 12-3-20; 8:45 am]
BILLING CODE 4910-13-P