Airworthiness Directives; Airbus SAS Airplanes, 71529-71532 [2020-24855]
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Rules and Regulations
Federal Register
Vol. 85, No. 218
Tuesday, November 10, 2020
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0970; Project
Identifier AD–2020–01359–T; Amendment
39–21305; AD 2020–22–09]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2001–16–
13, which applied to certain Airbus SAS
Model A330 series airplanes. AD 2001–
16–13 required a roto-test inspection of
fastener holes of certain fuselage joints
for cracks, reinforcement of the fuselage
between certain frames, and, if
necessary, a high frequency eddy
current (HFEC) inspection and repair.
As published, the applicability of AD
2001–16–13 inadvertently identified the
model designations as serial numbers.
This document corrects that error. This
new AD requires a roto-test inspection
of fastener holes of certain fuselage
joints for cracks, reinforcement of the
fuselage, and, if necessary, an HFEC
inspection and repair. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November
25, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 25, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of September 7, 2001 (66 FR
44295, August 23, 2001).
The FAA must receive comments on
this AD by December 28, 2020.
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SUMMARY:
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You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• 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.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For material incorporated by reference
(IBR) in this AD, contact Airbus SAS,
Airworthiness Office—EAL, Rond-Point
Emile Dewoitine No: 2, 31700 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Airworthiness
Products Section, Operational Safety
Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0970.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0970; 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, any comments
received, and other information. The
street address for the Docket Operations
office is listed above. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3229; email
Vladimir.Ulyanov@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
The FAA issued AD 2001–16–13,
Amendment 39–12382 (66 FR 44295,
August 23, 2001) (‘‘AD 2001–16–13’’),
which applied to certain Model A330
series airplanes. AD 2001–16–13 was
prompted by a report that during fatigue
testing on the fuselage, cracks were
detected in the longitudinal buttstrap at
stringer 9, at frame 31, and at frame
37.1. AD 2001–16–13 required a rototest inspection of fastener holes of
certain fuselage joints for cracks,
reinforcement of the fuselage between
frames 31 and 37.1, and, if necessary, an
HFEC inspection and repair. The FAA
issued AD 2001–16–13 to address
fatigue cracking of the fuselage
longitudinal buttstrap, which could
result in reduced structural integrity of
the fuselage.
Actions Since AD 2001–16–13 Was
Issued
Since the FAA issued AD 2001–16–
13, the FAA received a report that the
applicability of AD 2001–16–13 does
not match the applicability of the
corresponding Direction Ge´ne´rale de
l’Aviation Civile (DGAC) AD: French
Airworthiness Directive 2001–075(B),
dated March 17, 2001, which is also
referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI.’’ The model designations
identified in the applicability of the
MCAI were inadvertently identified as
serial numbers in the applicability of
AD 2001–16–13.
You may examine the MCAI in the
AD docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0970.
This AD was prompted by a report of
an error in the applicability of AD 2001–
16–13. The FAA has determined the
applicability must be revised to correct
the error. There are no affected U.S.
registered airplanes; however, an
affected airplane might be imported and
placed on the U.S. Register in the future.
The FAA is issuing this AD to address
fatigue cracking of the fuselage
longitudinal buttstrap, which could
result in reduced structural integrity of
the fuselage.
Since the FAA issued AD 2001–16–
13, the FAA has reviewed Airbus
Service Bulletin A330–53–3090,
Revision 03, dated December 11, 2002
(the FAA referred to Airbus Service
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Bulletin A330–53–3090, Revision 02,
dated January 9, 2001, as the
appropriate source of service
information for accomplishing the
actions required by AD 2001–16–13).
Airbus Service Bulletin A330–53–3090,
Revision 03, dated December 11, 2002,
clarifies certain inspection areas and
specifies no additional work is needed
for airplanes modified by a previous
revision. The FAA has determined
Airbus Service Bulletin A330–53–3090,
Revision 03, dated December 11, 2002,
is an appropriate source of service
information for accomplishing the
required actions of this AD.
Related IBR Material Under 1 CFR Part
51
Airbus Service Bulletin A330–53–
3090, Revision 03, dated December 11,
2002. This service information describes
procedures for a roto-test inspection of
fastener holes of certain fuselage joints
for cracks, reinforcement of the fuselage
between frames 31 and 37.1, and, if
necessary, an HFEC inspection.
This AD also requires Airbus Service
Bulletin A330–53–3090, Revision 02,
dated January 9, 2001, which the
Director of the Federal Register
approved for incorporation by reference
as of September 7, 2001 (66 FR 44295,
August 23, 2001).
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.
FAA’s Determination
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the State
of Design Authority, the FAA has been
notified of the unsafe condition
described in the MCAI and service
information referenced above. The FAA
is issuing this AD because the FAA
evaluated all pertinent information and
determined the unsafe condition exists
and is likely to exist or develop on other
products of the same type design.
Requirements of This AD
This AD requires a roto-test
inspection of fastener holes of certain
fuselage joints for cracks, reinforcement
of the fuselage between frames 31 and
37.1, and, if necessary, an HFEC
inspection and repair.
FAA’s Justification and Determination
of the Effective Date
There are currently no domestic
operators of these products. Therefore,
the FAA finds 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.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
the FAA did not precede it by notice
and opportunity for public comment.
The FAA invites you to send any
written relevant data, views, or
arguments about this AD. Send your
comments to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2020–0970; Project Identifier AD–
2020–01359–T’’ 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. 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 consider all
comments received by the closing date
and may amend this AD based on those
comments.
The FAA will post all comments the
FAA receives, 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 the FAA receives about this AD.
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 AD 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 AD,
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 AD. Submissions containing CBI
should be sent to the person identified
in the FOR FURTHER INFORMATION
CONTACT section. 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 (RFA)
The requirements of the 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
Currently, there are no affected U.S.registered airplanes. If an affected
airplane is imported and placed on the
U.S. Register in the future, the FAA
provides the following cost estimates to
comply with this AD:
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ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per
product
377 work-hours × $85 per hour = $32,045 .............................................................................................................
$6,187
$38,232
The FAA has received no definitive
data on which to base the cost estimates
for the on-condition actions specified in
this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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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
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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
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develop on products identified in this
rulemaking action.
Regulatory Findings
The FAA 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,
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.
Adoption of 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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing airworthiness directive
(AD) 2001–16–13, Amendment 39–
12382 (66 FR 44295, August 23, 2001),
and
■ b. Adding the following new AD:
■
■
2020–22–09 Airbus SAS: Amendment 39–
21305; Docket No. FAA–2020–0970;
Project Identifier AD–2020–01359–T.
(a) Effective Date
This AD is effective November 25, 2020.
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(b) Affected ADs
This AD replaces AD 2001–16–13,
Amendment 39–12382 (66 FR 44295, August
23, 2001) (‘‘AD 2001–16–13’’).
(c) Applicability
This AD applies to Airbus SAS Model
A330–301, –321, –322, –323, –341, –342, and
–343 airplanes, certificated in any category,
except airplanes on which Airbus Industrie
Modification 46636 has been accomplished
in production or which have been modified
in service as specified in Airbus Service
Bulletin A330–53–3090.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
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(e) Reason
This AD was prompted by a report that
during fatigue testing on the fuselage, cracks
were detected in the longitudinal buttstrap at
stringer 9, at frame 31, and at frame 37.1. The
FAA is issuing this AD to address fatigue
cracking of the fuselage longitudinal
buttstrap, which could result in reduced
structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection, with New Service
Information
This paragraph restates the requirements of
paragraph (a) of AD 2001–16–13, with new
service information. Prior to the
accumulation of 15,000 total flight cycles:
Perform a roto-test inspection to detect cracks
of the fastener holes at frame 31, frame 37.1,
and stringer 9, in accordance with Airbus
Service Bulletin A330–53–3090, Revision 02,
dated January 9, 2001; or Airbus Service
Bulletin A330–53–3090, Revision 03, dated
December 11, 2002.
(h) Retained Reinforcement, With New
Service Information
This paragraph restates the requirements of
paragraph (b) of AD 2001–16–13, with new
service information. If no cracks are detected
during the inspection performed in
accordance with paragraph (g) of this AD,
prior to further flight, reinforce the fuselage
structure between frames 31 and 37.1, in
accordance with Airbus Service Bulletin
A330–53–3090, Revision 02, dated January 9,
2001; or Airbus Service Bulletin A330–53–
3090, Revision 03, dated December 11, 2002.
(i) Retained Follow-Up Inspection and
Repair, With New Service Information and
Revised Repair Approval Language
This paragraph restates the requirements of
paragraph (c) of AD 2001–16–13, with new
service information and revised repair
approval language. If any crack is detected
during the inspection performed in
accordance with paragraph (g) of this AD,
prior to further flight, perform a high
frequency eddy current (HFEC) inspection to
determine the crack length, in accordance
with Airbus Service Bulletin A330–53–3090,
Revision 02, dated January 9, 2001; or Airbus
Service Bulletin A330–53–3090, Revision 03,
dated December 11, 2002. Prior to further
flight, repair the crack in accordance with a
method approved by the Direction Ge´ne´rale
de l’Aviation Civile (or its delegated agent) or
using a method approved by the Manager,
Large Aircraft Section, International
Validation Branch, FAA; or the European
Union Aviation Safety Agency (EASA); or
Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
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71531
Section, International Validation 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 responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (k)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or the
European Union Aviation Safety Agency
(EASA); or Airbus SAS’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (j)(2) of this AD: If
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) French
airworthiness directive 2001–075(B), dated
March 17, 2001, for related information. This
MCAI may be found in the AD docket on the
internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2020–0970.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3229; email
Vladimir.Ulyanov@faa.gov.
(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 this AD specifies otherwise.
(3) The following service information was
approved for IBR on November 25, 2020.
(i) Airbus Service Bulletin A330–53–3090,
Revision 03, dated December 11, 2002.
(ii) [Reserved]
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(4) The following service information was
approved for IBR on September 7, 2001 (66
FR 44295, August 23, 2001).
(i) Airbus Service Bulletin A330–53–3090,
Revision 02, dated January 9, 2001.
(ii) [Reserved]
(5) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; email airworthiness.A330-A340@
airbus.com; internet https://www.airbus.com.
(6) You may view this service information
at the FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South 216th
St., Des Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(7) 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 fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on October 26, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–24855 Filed 11–9–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0687; Project
Identifier AD–2020–00571–E; Amendment
39–21314; AD 2020–22–18]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Corporation (Type Certificate
Previously Held by Allison Engine
Company) Turboprop Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Rolls-Royce Corporation (RRC) AE
2100A, AE 2100D2, AE 2100D2A, and
AE 2100P model turboprop engines.
This AD was prompted by a report of a
propeller gearbox (PGB) development
test conducted by the manufacturer, in
which high vibration occurred due to a
fatigue crack that initiated in the PGB
shaft and carrier assembly. This AD
requires assignment of usage hours to
the PGB shaft and carrier assembly at
the next engine shop visit and
replacement of PGB shaft and carrier
assemblies prior to exceeding the new
life limits established by the
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SUMMARY:
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manufacturer. The FAA is issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective December
15, 2020.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 15, 2020.
ADDRESSES: For service information
identified in this final rule, contact
Rolls-Royce Corporation, 450 South
Meridian Street, Mail Code NB–01–06,
Indianapolis, IN 46225; phone: 317–
230–1667; email: CMSEindyOSD@rollsroyce.com; internet: www.rollsroyce.com. 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 on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0687.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0687; 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 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: Kyri
Zaroyiannis, Aerospace Engineer,
Chicago ACO Branch, FAA, 2300 East
Devon Avenue, Des Plaines, IL 60018;
phone: 847–294–7836; fax: 847–294–
7834; email: kyri.zaroyiannis@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all RRC AE 2100A, AE 2100D2,
AE 2100D2A, and AE 2100P model
turboprop engines. The NPRM
published in the Federal Register on
August 11, 2020 (85 FR 48482). The
NPRM was prompted by a report of a
PGB development test conducted by the
manufacturer, in which high vibration
occurred due to a fatigue crack that
initiated in the PGB shaft and carrier
assembly. In the NPRM, the FAA
proposed to require the assignment of
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usage hours to the PGB shaft and carrier
assembly at the next engine shop visit
and replacement of PGB shaft and
carrier assemblies before exceeding the
new life limits established by the
manufacturer. The FAA is issuing this
AD to address the unsafe condition on
these products.
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA received no
comments on the NPRM or on the
determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data
and determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. The FAA has determined that
these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
The FAA reviewed RRC Alert Service
Bulletin (ASB) AE 2100A–A–72–322/AE
2100P–A–72–047, Revision 1 (single
document), dated May 11, 2018, and
RRC ASB AE 2100D2–A–72–111/AE
2100D3–A–72–313/AE 2100J–A–72–
111, Revision 1 (single document),
dated May 28, 2018. RRC ASB AE
2100A–A–72–322/AE 2100P–A–72–047
describes procedures for assigning usage
hours to the PGB shaft and carrier
assemblies on RRC AE 2100A and AE
2100P model engines. RRC ASB AE
2100D2–A–72–111/AE 2100D3–A–72–
313/AE 2100J–A–72–111 describes
procedures for verifying the PGB shaft
and carrier assembly serial numbers and
assigning usage hours to the PGB shaft
and carrier assemblies on RRC AE
2100D2 and AE 2100D2A model
engines. 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
The FAA reviewed Task 05–10–00–
800–801 of RRC AE 2100A Engine
Maintenance Manual (MM) CSP31005,
Revision 57, dated August 15, 2019, and
Task 05–12–11–800–802 of RRC AE
2100A Engine MM CSP31005, Revision
57, dated August 15, 2019. Task 05–10–
00–800–801 of RRC AE 2100A Engine
MM provides information for
E:\FR\FM\10NOR1.SGM
10NOR1
]]>Agencies
[Federal Register Volume 85, Number 218 (Tuesday, November 10, 2020)]
[Rules and Regulations]
[Pages 71529-71532]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-24855]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 85, No. 218 / Tuesday, November 10, 2020 /
Rules and Regulations
[[Page 71529]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0970; Project Identifier AD-2020-01359-T;
Amendment 39-21305; AD 2020-22-09]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2001-16-
13, which applied to certain Airbus SAS Model A330 series airplanes. AD
2001-16-13 required a roto-test inspection of fastener holes of certain
fuselage joints for cracks, reinforcement of the fuselage between
certain frames, and, if necessary, a high frequency eddy current (HFEC)
inspection and repair. As published, the applicability of AD 2001-16-13
inadvertently identified the model designations as serial numbers. This
document corrects that error. This new AD requires a roto-test
inspection of fastener holes of certain fuselage joints for cracks,
reinforcement of the fuselage, and, if necessary, an HFEC inspection
and repair. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective November 25, 2020.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 25,
2020.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
September 7, 2001 (66 FR 44295, August 23, 2001).
The FAA must receive comments on this AD by December 28, 2020.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
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.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For material incorporated by reference (IBR) in this AD, contact
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 45 80; email [email protected]; internet https://www.airbus.com. You may view this referenced service information at the
FAA, Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability of
this material at the FAA, call 206-231-3195. It is also available on
the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2020-0970.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0970; 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, any comments received, and other information. The
street address for the Docket Operations office is listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
Large Aircraft Section, International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3229;
email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued AD 2001-16-13, Amendment 39-12382 (66 FR 44295,
August 23, 2001) (``AD 2001-16-13''), which applied to certain Model
A330 series airplanes. AD 2001-16-13 was prompted by a report that
during fatigue testing on the fuselage, cracks were detected in the
longitudinal buttstrap at stringer 9, at frame 31, and at frame 37.1.
AD 2001-16-13 required a roto-test inspection of fastener holes of
certain fuselage joints for cracks, reinforcement of the fuselage
between frames 31 and 37.1, and, if necessary, an HFEC inspection and
repair. The FAA issued AD 2001-16-13 to address fatigue cracking of the
fuselage longitudinal buttstrap, which could result in reduced
structural integrity of the fuselage.
Actions Since AD 2001-16-13 Was Issued
Since the FAA issued AD 2001-16-13, the FAA received a report that
the applicability of AD 2001-16-13 does not match the applicability of
the corresponding Direction G[eacute]n[eacute]rale de l'Aviation Civile
(DGAC) AD: French Airworthiness Directive 2001-075(B), dated March 17,
2001, which is also referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI.'' The model designations
identified in the applicability of the MCAI were inadvertently
identified as serial numbers in the applicability of AD 2001-16-13.
You may examine the MCAI in the AD docket on the internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2020-0970.
This AD was prompted by a report of an error in the applicability
of AD 2001-16-13. The FAA has determined the applicability must be
revised to correct the error. There are no affected U.S. registered
airplanes; however, an affected airplane might be imported and placed
on the U.S. Register in the future. The FAA is issuing this AD to
address fatigue cracking of the fuselage longitudinal buttstrap, which
could result in reduced structural integrity of the fuselage.
Since the FAA issued AD 2001-16-13, the FAA has reviewed Airbus
Service Bulletin A330-53-3090, Revision 03, dated December 11, 2002
(the FAA referred to Airbus Service
[[Page 71530]]
Bulletin A330-53-3090, Revision 02, dated January 9, 2001, as the
appropriate source of service information for accomplishing the actions
required by AD 2001-16-13). Airbus Service Bulletin A330-53-3090,
Revision 03, dated December 11, 2002, clarifies certain inspection
areas and specifies no additional work is needed for airplanes modified
by a previous revision. The FAA has determined Airbus Service Bulletin
A330-53-3090, Revision 03, dated December 11, 2002, is an appropriate
source of service information for accomplishing the required actions of
this AD.
Related IBR Material Under 1 CFR Part 51
Airbus Service Bulletin A330-53-3090, Revision 03, dated December
11, 2002. This service information describes procedures for a roto-test
inspection of fastener holes of certain fuselage joints for cracks,
reinforcement of the fuselage between frames 31 and 37.1, and, if
necessary, an HFEC inspection.
This AD also requires Airbus Service Bulletin A330-53-3090,
Revision 02, dated January 9, 2001, which the Director of the Federal
Register approved for incorporation by reference as of September 7,
2001 (66 FR 44295, August 23, 2001).
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.
FAA's Determination
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to the FAA's bilateral agreement with the State of Design Authority,
the FAA has been notified of the unsafe condition described in the MCAI
and service information referenced above. The FAA is issuing this AD
because the FAA evaluated all pertinent information and determined the
unsafe condition exists and is likely to exist or develop on other
products of the same type design.
Requirements of This AD
This AD requires a roto-test inspection of fastener holes of
certain fuselage joints for cracks, reinforcement of the fuselage
between frames 31 and 37.1, and, if necessary, an HFEC inspection and
repair.
FAA's Justification and Determination of the Effective Date
There are currently no domestic operators of these products.
Therefore, the FAA finds 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.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and the FAA did not precede it by notice and opportunity for
public comment. The FAA invites you to send any written relevant data,
views, or arguments about this AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2020-0970;
Project Identifier AD-2020-01359-T'' 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. 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 consider all comments received by the closing
date and may amend this AD based on those comments.
The FAA will post all comments the FAA receives, 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 the FAA receives about this AD.
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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to the
person identified in the FOR FURTHER INFORMATION CONTACT section. 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 (RFA)
The requirements of the 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
Currently, there are no affected U.S.-registered airplanes. If an
affected airplane is imported and placed on the U.S. Register in the
future, the FAA provides the following cost estimates to comply with
this AD:
Estimated Costs for Required Actions
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
377 work-hours x $85 per hour = $6,187 $38,232
$32,045..............................
------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions specified in this AD.
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
[[Page 71531]]
develop on products identified in this rulemaking action.
Regulatory Findings
The FAA 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, 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.
Adoption of 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) 2001-16-13, Amendment 39-12382
(66 FR 44295, August 23, 2001), and
0
b. Adding the following new AD:
2020-22-09 Airbus SAS: Amendment 39-21305; Docket No. FAA-2020-0970;
Project Identifier AD-2020-01359-T.
(a) Effective Date
This AD is effective November 25, 2020.
(b) Affected ADs
This AD replaces AD 2001-16-13, Amendment 39-12382 (66 FR 44295,
August 23, 2001) (``AD 2001-16-13'').
(c) Applicability
This AD applies to Airbus SAS Model A330-301, -321, -322, -323,
-341, -342, and -343 airplanes, certificated in any category, except
airplanes on which Airbus Industrie Modification 46636 has been
accomplished in production or which have been modified in service as
specified in Airbus Service Bulletin A330-53-3090.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report that during fatigue testing on
the fuselage, cracks were detected in the longitudinal buttstrap at
stringer 9, at frame 31, and at frame 37.1. The FAA is issuing this
AD to address fatigue cracking of the fuselage longitudinal
buttstrap, which could result in reduced structural integrity of the
fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection, with New Service Information
This paragraph restates the requirements of paragraph (a) of AD
2001-16-13, with new service information. Prior to the accumulation
of 15,000 total flight cycles: Perform a roto-test inspection to
detect cracks of the fastener holes at frame 31, frame 37.1, and
stringer 9, in accordance with Airbus Service Bulletin A330-53-3090,
Revision 02, dated January 9, 2001; or Airbus Service Bulletin A330-
53-3090, Revision 03, dated December 11, 2002.
(h) Retained Reinforcement, With New Service Information
This paragraph restates the requirements of paragraph (b) of AD
2001-16-13, with new service information. If no cracks are detected
during the inspection performed in accordance with paragraph (g) of
this AD, prior to further flight, reinforce the fuselage structure
between frames 31 and 37.1, in accordance with Airbus Service
Bulletin A330-53-3090, Revision 02, dated January 9, 2001; or Airbus
Service Bulletin A330-53-3090, Revision 03, dated December 11, 2002.
(i) Retained Follow-Up Inspection and Repair, With New Service
Information and Revised Repair Approval Language
This paragraph restates the requirements of paragraph (c) of AD
2001-16-13, with new service information and revised repair approval
language. If any crack is detected during the inspection performed
in accordance with paragraph (g) of this AD, prior to further
flight, perform a high frequency eddy current (HFEC) inspection to
determine the crack length, in accordance with Airbus Service
Bulletin A330-53-3090, Revision 02, dated January 9, 2001; or Airbus
Service Bulletin A330-53-3090, Revision 03, dated December 11, 2002.
Prior to further flight, repair the crack in accordance with a
method approved by the Direction G[eacute]n[eacute]rale de
l'Aviation Civile (or its delegated agent) or using a method
approved by the Manager, Large Aircraft Section, International
Validation Branch, FAA; or the European Union Aviation Safety Agency
(EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
(j) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Large Aircraft Section, International Validation 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 responsible Flight
Standards Office, as appropriate. If sending information directly to
the Large Aircraft Section, International Validation Branch, send it
to the attention of the person identified in paragraph (k)(2) of
this AD. Information may be emailed to: [email protected].
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, Large Aircraft
Section, International Validation Branch, FAA; or the European Union
Aviation Safety Agency (EASA); or Airbus SAS's EASA DOA. If approved
by the DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (j)(2) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) French airworthiness directive 2001-075(B), dated March 17,
2001, for related information. This MCAI may be found in the AD
docket on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2020-0970.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198;
telephone and fax 206-231-3229; email [email protected].
(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 this AD specifies otherwise.
(3) The following service information was approved for IBR on
November 25, 2020.
(i) Airbus Service Bulletin A330-53-3090, Revision 03, dated
December 11, 2002.
(ii) [Reserved]
[[Page 71532]]
(4) The following service information was approved for IBR on
September 7, 2001 (66 FR 44295, August 23, 2001).
(i) Airbus Service Bulletin A330-53-3090, Revision 02, dated
January 9, 2001.
(ii) [Reserved]
(5) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 45 80; email [email protected];
internet https://www.airbus.com.
(6) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability
of this material at the FAA, call 206-231-3195.
(7) 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 October 26, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-24855 Filed 11-9-20; 8:45 am]
BILLING CODE 4910-13-P
