Airworthiness Directives; Airbus SAS Airplanes, 26781-26785 [2019-11896]
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Boeing Service Bulletin 737–28A1216, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–20, whichever is later.
(iv) For AWL No. 28–AWL–21, ‘‘Auxiliary
Tank Fuel Boost Pump Automatic Shutoff
System’’: Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1216, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–21, whichever is later.
(v) For AWL No. 28–AWL–22, ‘‘OverCurrent and Arcing Protection Electrical
Design Features Operation—Boost Pump
Ground Fault Interrupter (GFI)’’: Within 12
months after accomplishment of the actions
specified in Boeing Service Bulletin 737–
28A1212, or within 12 months after the most
recent inspection was performed as specified
in AWL No. 28–AWL–22, whichever is later.
(vi) For AWL No. 28–AWL–23, ‘‘Center
Tank Fuel Boost Pump Power Failed On
Protection System’’: Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1227, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–23, whichever is later.
(vii) For AWL No. 28–AWL–24, ‘‘Auxiliary
Fuel Tank Boost Pump Power Failed On
Protection System’’: Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1227, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–24, whichever is later.
(viii) For AWL No. 28–AWL–27, ‘‘AC Fuel
Boost Pump Installation’’: Within 72 months
after the most recent inspection was
performed as specified in AWL No. 28–
AWL–27, or within 12 months after the
effective date of this AD if no inspection has
been performed in the last 72 months.
(ix) For AWL No. 28–AWL–31, ‘‘Cushion
Clamps and Teflon Sleeving Installed on Outof-Tank Wire Bundles Installed on Brackets
that are Mounted Directly on the Fuel
Tanks’’: Within 144 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1228.
(x) For AWL No. 47–AWL–04, ‘‘Nitrogen
Generation System (NGS)—Thermal Switch’’:
Within 22,500 flight hours after
accomplishment of the actions specified in
Boeing Service Bulletin 737–47–1005; within
22,500 flight hours after accomplishment of
the actions specified in Boeing Service
Bulletin 737–47–1008; or within 22,500 flight
hours after the most recent inspection was
performed as specified in AWL No. 47–
AWL–04; whichever is latest.
(xi) For AWL No. 47–AWL–05, ‘‘Nitrogen
Generation System (NGS)—Nitrogen
Enriched Air (NEA) Distribution Ducting
Integrity’’: Within 14,500 flight hours after
accomplishment of the actions specified in
Boeing Service Bulletin 737–47–1005; within
14,500 flight hours after accomplishment of
the actions specified in Boeing Service
Bulletin 737–47–1008; or within 14,500 flight
hours after the most recent inspection was
performed as specified in AWL No. 47–
AWL–05; whichever is latest.
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(h) Additional Acceptable Wire Types and
Sleeving
As an option, when accomplishing the
actions required by paragraph (g) of this AD,
the changes specified in paragraphs (h)(1)
and (h)(2) of this AD are acceptable.
(1) Where AWL No. 28–AWL–05 identifies
wire types BMS 13–48, BMS 13–58, and BMS
13–60, the following wire types are
acceptable: MIL–W–22759/16, SAE
AS22759/16 (M22759/16), MIL–W–22759/32,
SAE AS22759/32 (M22759/32), MIL–W–
22759/34, SAE AS22759/34 (M22759/34),
MIL–W–22759/41, SAE AS22759/41
(M22759/41), MIL–W–22759/86, SAE
AS22759/86 (M22759/86), MIL–W–22759/87,
SAE AS22759/87 (M22759/87), MIL–W–
22759/92, and SAE AS22759/92 (M22759/
92); and MIL–C–27500 and NEMA WC 27500
cables constructed from these military or
SAE specification wire types, as applicable.
(2) Where AWL No. 28–AWL–05 identifies
TFE–2X Standard wall for wire sleeving, the
following sleeving materials are acceptable:
Roundit 2000NX and Varglas Type HO, HP,
or HM.
(i) No Alternative Actions, Intervals, or
Critical Design Configuration Control
Limitations (CDCCLs)
After the existing maintenance or
inspection program has been revised as
required by paragraph (g) of this AD, no
alternative actions (e.g., inspections),
intervals, or CDCCLs may be used unless the
actions, intervals, and CDCCLs are approved
as an alternative method of compliance
(AMOC) in accordance with the procedures
specified in paragraph (k) of this AD.
(j) Terminating Actions for Certain AD
Requirements
Accomplishment of the revision required
by paragraph (g) of this AD terminates the
requirements specified in paragraphs (j)(1)
through (j)(6) of this AD for that airplane:
(1) All requirements of AD 2008–10–09 R1.
(2) The revision required by paragraph (l)
of AD 2011–12–09.
(3) The revision required by paragraph (h)
of AD 2013–13–15.
(4) The revision required by paragraph (j)
of AD 2013–25–05.
(5) The revisions required by paragraphs (l)
and (n) of AD 2016–18–16.
(6) The revision required by paragraph (h)
of AD 2017–17–09.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or local Flight Standards
District Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (l)(2) of
this AD. Information may be emailed to: 9ANM-LAACO-AMOC-Requests@faa.gov.
(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.
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(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO Branch, FAA, to make those findings.
To be approved, the repair method,
modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(l) Related Information
(1) For more information about this AD,
contact Jeffrey Rothman, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines,
WA 98198; phone and fax: 206–231–3558;
email: jeffrey.rothman@faa.gov.
(2) For information about AMOCs, contact
Serj Harutunian, Aerospace Engineer,
Propulsion Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5254; fax: 562–627–5210; email:
serj.harutunian@faa.gov.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
phone: 562–797–1717; internet: https://
www.myboeingfleet.com. You may view this
service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
Issued in Des Moines, Washington, on May
20, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–11925 Filed 6–7–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0402; Product
Identifier 2019–NM–008–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2005–17–
14, which applies to all Airbus SAS
Model A300 series airplanes; Model
A300 B4–600, B4–600R, and F4–600R
series airplanes, and Model A300 C4–
SUMMARY:
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605R Variant F airplanes (collectively
called Model A300–600 series
airplanes); and Model A310 series
airplanes. AD 2005–17–14 requires
repetitive tests to detect
desynchronization of the rudder servo
actuators, and adjustment or
replacement of the spring rods of the
rudder servo actuators, if necessary. AD
2005–17–14 also requires repetitive
tests/inspections/analyses of the rudder
servo actuators, and related
investigative/corrective actions if
necessary. Since we issued AD 2005–
17–14, analyses of the inspection results
indicated that the assumptions made to
establish the survey campaign were not
adequate, and a new investigation
determined the existing inspection
procedures and compliance times do
not adequately address the unsafe
condition. This proposed AD would
retain some requirements of AD 2005–
17–14 and revise the inspection
procedures and compliance times, as
specified in an European Aviation
Safety Agency (EASA) AD, which will
be incorporated by reference. We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by July 25, 2019.
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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For the incorporation by reference
(IBR) material described in the ‘‘Related
IBR material under 1 CFR part 51’’
section in SUPPLEMENTARY INFORMATION,
contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany;
telephone +49 221 89990 1000; email
ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
IBR material on the EASA website at
https://ad.easa.europa.eu. You may
view this IBR material at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
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It is also available in the AD docket on
the internet at https://
www.regulations.gov.
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–2019–
0402; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(telephone 800–647–5527) is listed
above. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3225.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2019–0402; Product Identifier 2019–
NM–008–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM based
on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this NPRM.
Discussion
We issued AD 2005–17–14,
Amendment 39–14235 (70 FR 50157,
August 26, 2005) (‘‘AD 2005–17–14’’),
for all Airbus SAS Model A300 series
airplanes, Model A300–600 series
airplanes, and Model A310 series
airplanes. AD 2005–17–14 requires
repetitive tests to detect
desynchronization of the rudder servo
actuators, and adjustment or
replacement of the spring rods of the
rudder servo actuators, if necessary; and
repetitive tests, inspections, and
analyses of the rudder servo actuators,
and related investigative and corrective
actions if necessary. AD 2005–17–14
resulted from new reports of
desynchronization of the rudder servo
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actuators. We issued AD 2005–17–14 to
address desynchronization of one of the
three rudder servo actuators, which, if
combined with an engine failure, could
result in the loss of the related hydraulic
system and could cause the loss of one
of the two synchronized actuators. This
condition could create additional
fatigue loading and possible cracking of
the attachment fittings and could result
in the inability of the remaining
synchronized actuator to maintain the
commanded rudder deflection, leading
to reduced controllability of the
airplane.
Actions Since AD 2005–17–14 Was
Issued
Since we issued AD 2005–17–14,
EASA reported that analyses of the
inspection results indicate that the
assumptions made in 2004 to establish
the survey campaign were not adequate.
This determination led to investigation
and revision of the service information
with revised inspection instructions and
compliance times, depending on
airplane configuration.
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2019–0017, dated January 29, 2019
(‘‘EASA AD 2019–0017’’) (also referred
to as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus SAS Model A300 series
airplanes, Model A300–600 series
airplanes, and Model A310 series
airplanes. The MCAI states:
Numerous occurrences were reported of
rudder servo control de-synchronization,
some of which had caused structural
damages to the fin or side fittings of the
rudder actuator attachments. Analyses
revealed that a de-synchronization of the
rudder servo control induced by
misalignment of the three servo controls, or
by thermal expansion, can provoke opposing
loads.
This condition, if not detected and
corrected, could induce failure of rudderassociated systems, possibly resulting in
reduced control of the aeroplane.
Previously, DGAC [Direction Ge´ne´rale de
l’Aviation Civile] France issued AD F–2004–
063 for A300–600ST aeroplanes, and AD F–
2004–092 (EASA approval 2004–6368)
[which corresponds to FAA AD 2005–17–14]
for A300, A310 and A300–600 aeroplanes, to
require repetitive inspections of rudder servo
controls, fin box and rudder structures, and,
depending on findings, accomplishment of
applicable corrective action(s).
Since those ADs were issued, analyses of
the inspection results indicate that the
assumptions made in 2004 to establish the
survey campaign were not adequate. This
determination induced new investigation and
ATA 55 SBs [service bulletins] revision with
new inspection instructions and new
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compliance times, depending on aeroplane
configuration.
For the reason described above, this
[EASA] AD retains partially the requirements
of DGAC France AD F–2004–063 and AD F–
2004–092 (EASA approval 2004–6368),
which are superseded, and requires the new
inspections (latest SB revision) at new
intervals.
The new repetitive intervals for the
inspections specified in paragraph (2) of
EASA AD 2019–0017 range from 300
flight cycles to 6,000 flight cycles,
depending on inspection type.
Explanation of Retained Requirements
Although this proposed AD does not
explicitly restate the requirements of AD
2005–17–14, this proposed AD would
retain certain requirements of AD 2005–
17–14. Those requirements are
referenced in EASA AD 2019–0017,
which, in turn, is referenced in
paragraph (g) of this proposed AD.
Related IBR Material Under 1 CFR Part
51
EASA AD 2019–0017 describes
procedures for repetitive inspections of
the rudder servo actuators and related
investigative/corrective actions. Related
investigative actions include repetitive
inspections of fin box and rudder servo
controls. Corrective actions include
repair. This material 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 and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI referenced above. We are
proposing this AD because we evaluated
all pertinent information and
determined an unsafe condition exists
and is likely to exist or develop on other
products of the same type design.
Proposed Requirements of This NPRM
This proposed AD would require
accomplishing the actions specified in
EASA AD 2019–0017 described
previously, as incorporated by
reference, except for any differences
identified as exceptions in the
regulatory text of this AD and except as
discussed under ‘‘Differences Between
this Proposed AD and the MCAI.’’
Explanation of Required Compliance
Information
In the FAA’s ongoing efforts to
improve the efficiency of the AD
process, the FAA worked with Airbus
and EASA to develop a process to use
certain EASA ADs as the primary source
of information for compliance with
requirements for corresponding FAA
ADs. As a result, EASA AD 2019–0017
will be incorporated by reference in the
FAA final rule. This proposed AD
would, therefore, require compliance
with the provisions specified in EASA
AD 2019–0017, except for any
differences identified as exceptions in
the regulatory text of this proposed AD.
Service information specified in EASA
AD 2019–0017 that is required for
compliance with EASA AD 2019–0017
will be available on the internet https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0402 after the FAA final rule is
published.
Differences Between This Proposed AD
and the MCAI
Where paragraph (4) of EASA AD
2019–0017 refers to ‘‘during any
inspection as required by paragraph (2)
of this AD,’’ this proposed AD would
require using ‘‘during any inspection as
required by paragraph (2) or (3) of this
AD.’’ EASA AD 2019–0017 did not
specify a corrective action for the
inspections required by paragraph (3) of
EASA AD 2019–0017.
Costs of Compliance
We estimate that this proposed AD
affects 133 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS *
Action
Labor cost
Retained actions from AD 2005–17–14 .........
New proposed actions ....................................
1 work-hour × $85 per hour = $85 .................
2 work-hours × $85 per hour = $85 ...............
Cost per
product
Parts cost
$0
0
$85
170
Cost on U.S.
operators
$11,305
22,610
* Table does not include estimated costs for reporting.
We estimate that it would take about
1 work-hour per product to comply with
the proposed reporting requirement in
this proposed AD. The average labor
rate is $85 per hour. Based on these
figures, we estimate the cost of reporting
the inspection results on U.S. operators
to be $11,305, or $85 per product.
We estimate the following costs to do
any necessary on-condition inspections
that would be required based on the
results of any required actions. We have
no way of determining the number of
aircraft that might need these oncondition actions:
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ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Cost per
product
34 work-hours × $85 per hour = $2,890 .................................................................................................................
$0
$2,890
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition repair
specified in this proposed AD.
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Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
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Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this NPRM is 2120–0056.
The paperwork cost associated with this
NPRM has been detailed in the Costs of
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Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this NPRM is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW, Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes and associated
appliances to the Director of the System
Oversight Division.
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Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the 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 this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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
removing Airworthiness Directive (AD)
2005–17–14, Amendment 39–14235 (70
FR 50157, August 26, 2005), and adding
the following new AD:
■
Airbus SAS: Docket No. FAA–2019–0402;
Product Identifier 2019–NM–008–AD.
(a) Comments Due Date
We must receive comments by July 25,
2019.
(b) Affected ADs
This AD replaces AD 2005–17–14,
Amendment 39–14235 (70 FR 50157, August
26, 2005) (‘‘AD 2005–17–14’’).
(c) Applicability
This AD applies to the Airbus SAS
airplanes, certificated in any category,
specified in paragraphs (c)(1) through (c)(3)
of this AD, as identified in European
Aviation Safety Agency (EASA) AD 2019–
0017, dated January 29, 2019 (‘‘EASA AD
2019–0017’’).
(1) Model A300 B2–1A, B2–1C, B2K–3C,
B2–203, B4–2C, B4–103, and B4–203
airplanes.
(2) Model A300 B4–601, B4–603, B4–620,
B4–622, B4–605R, B4–622R, F4–605R and
F4–622R airplanes, and Model A300 C4–
605R Variant F airplanes.
(3) Model A310–203, –204, –221, –222,
–304, –322, –324, and –325 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls; 55,
Stabilizers.
(e) Reason
This AD was prompted by reports of
desynchronization of the rudder servo
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actuators. We are issuing this AD to address
desynchronization of one of the three rudder
servo actuators, which, if combined with an
engine failure, could result in the loss of the
related hydraulic system and could cause the
loss of one of the two synchronized actuators.
This condition could create additional
fatigue loading and possible cracking of the
attachment fittings and could result in the
inability of the remaining synchronized
actuator to maintain the commanded rudder
deflection, leading to reduced controllability
of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2019–0017.
(h) Exceptions to EASA AD 2019–0017
(1) For purposes of determining
compliance with the requirements of this AD:
Where EASA AD 2019–0017 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) For purposes of determining
compliance with the requirements of this AD:
Where paragraph (1) of EASA AD 2019–0017
specifies ‘‘after the last inspection as
previously required by DGAC France AD F–
2004–092,’’ this AD requires using ‘‘after the
most recent inspection done as specified in
Airbus Service Bulletin A300–27–0188,
Revision 2, dated October 1, 1997; A300–27–
6036, Revision 2, dated October 1, 1997;
A300–55–0044, dated October 22, 1996;
A300–55–6023, dated October 22, 1996;
A310–27–2082, Revision 2, dated October 1,
1997; or A310–55–2026, dated October 22,
1996.’’
(3) For purposes of determining
compliance with the requirements of this AD:
Where paragraph (1) of EASA AD 2019–0017
refers to ‘‘the 03 July 2004,’’ this AD requires
using ‘‘September 30, 2005’’ (the effective
date of AD 2005–17–14).
(4) For purposes of determining
compliance with the requirements of this AD:
Where paragraph (4) of EASA AD 2019–0017
refers to ‘‘during any inspection as required
by paragraph (2) of this AD,’’ this AD
requires using ‘‘during any inspection as
required by paragraph (2) or (3) of this AD.’’
(5) Where any service information
referenced in EASA AD 2019–0017 specifies
reporting, this AD requires reporting all
inspection results at the applicable time
specified in paragraph (h)(5)(i) or (h)(5)(ii) of
this AD. If operators have reported findings
as part of obtaining any corrective actions
approved by Airbus SAS’s EASA Design
Organization Approval (DOA), operators are
not required to report those findings as
specified in this paragraph.
(i) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(ii) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
E:\FR\FM\10JNP1.SGM
10JNP1
Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules
khammond on DSKBBV9HB2PROD with PROPOSALS
(6) The ‘‘Remarks’’ section of EASA AD
2019–0017 does not apply to this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards 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 International Section, send it
to the attention of the person identified in
paragraph (j)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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.
(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, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): For any
service information referenced in EASA AD
2019–0017 that contains RC procedures and
tests: Except as required by paragraph (i)(2)
of this AD, RC 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.
(4) Paperwork Reduction Act Burden
Statement: A federal agency may not conduct
or sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 1 hour per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW, Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
VerDate Sep<11>2014
16:18 Jun 07, 2019
Jkt 247001
(j) Related Information
(1) For information about EASA AD 2019–
0017, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone
+49 221 89990 6017; email ADs@
easa.europa.eu; Internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu. You may view this EASA
AD at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
EASA AD 2019–0017 may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2019–0402.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3225.
Issued in Des Moines, Washington, on May
28, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–11896 Filed 6–7–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF THE INTERIOR
Bureau of Indian Affairs
25 CFR Part 30
[190D0102DR/DS5A300000/
DR.5A311.IA000119]
RIN 1076–AF13
Standards, Assessments, and
Accountability System
AGENCY:
Bureau of Indian Affairs,
Interior.
Proposed rule and Tribal
consultation.
ACTION:
The Bureau of Indian
Education (BIE) is proposing a rule
developed using a negotiated
rulemaking process, as required by the
2015 Every Student Succeeds Act
(ESSA), for implementation of the
Secretary of the Interior’s obligation to
define the standards, assessments, and
accountability system consistent with
ESSA for BIE-funded schools.
DATES: Please submit comments by
August 9, 2019. Please see ‘‘V.
Consultation Schedule’’ of this
preamble for dates of consultation
sessions on this proposed rule.
ADDRESSES: You may submit comments
by any of the following methods:
Federal rulemaking portal: https://
www.regulations.gov. The rule is listed
under the agency name ‘‘Bureau of
SUMMARY:
PO 00000
Frm 00019
Fmt 4702
Sfmt 4702
26785
Indian Affairs’’ under Docket BIA–
2016–0005.
Email: comments@bia.gov. Include
the number 1076–AF13 in the subject
line of the message.
Mail: Elizabeth Appel, Office of
Regulatory Affairs & Collaborative
Action, U.S. Department of the Interior,
1849 C Street NW, Mail Stop 4660,
Washington, DC 20240. Include the
number 1076–AF13 in the subject line
of the message.
Hand delivery: Elizabeth Appel,
Office of Regulatory Affairs &
Collaborative Action, U.S. Department
of the Interior, 1849 C Street NW, Mail
Stop 4660, Washington, DC 20240.
Include the number 1076–AF13 in the
subject line of the message.
Docket: For access to the docket to
read background documents or
comments received, go to https://
www.regulations.gov and search for
Docket Number BIA–2016–0005. We
cannot ensure that comments received
after the close of the comment period
(see DATES) will be included in the
docket for this rulemaking and
considered.
Comments on the information
collections contained in this proposed
regulation (see ‘‘Paperwork Reduction
Act’’ section, below) are separate from
those on the substance of the rule. Send
comments on the information collection
burden to OMB by facsimile to (202)
395–5806 or email to the OMB Desk
Officer for the Department of the
Interior at OIRA_DOCKET@
omb.eop.gov. Please send a copy of your
comments to the person listed in the
FOR FURTHER INFORMATION CONTACT
section of this notice.
Please see ‘‘V. Consultation
Schedule’’ of this preamble for
addresses of consultation sessions on
this proposed rule.
FOR FURTHER INFORMATION CONTACT:
Elizabeth Appel, Director, Office of
Regulatory Affairs & Collaborative
Action, (202) 273–4680;
elizabeth.appel@bia.gov.
SUPPLEMENTARY INFORMATION:
I. Background
II. General Description of the Proposed Rule
III. Section-by-Section Analysis
IV. Other Proposed Changes Under
Consideration
V. Consultation Schedule
VI. Procedural Requirements
A. Regulatory Planning and Review (E.O.
12866 and 13563)
B. Reducing Regulation and Controlling
Regulatory Costs (E.O. 13771)
C. Regulatory Flexibility Act
D. Small Business Regulatory Enforcement
Fairness Act
E. Unfunded Mandates Reform Act
F. Takings (E.O. 12630)
E:\FR\FM\10JNP1.SGM
10JNP1
]]>Agencies
[Federal Register Volume 84, Number 111 (Monday, June 10, 2019)]
[Proposed Rules]
[Pages 26781-26785]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-11896]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0402; Product Identifier 2019-NM-008-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2005-17-
14, which applies to all Airbus SAS Model A300 series airplanes; Model
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-
[[Page 26782]]
605R Variant F airplanes (collectively called Model A300-600 series
airplanes); and Model A310 series airplanes. AD 2005-17-14 requires
repetitive tests to detect desynchronization of the rudder servo
actuators, and adjustment or replacement of the spring rods of the
rudder servo actuators, if necessary. AD 2005-17-14 also requires
repetitive tests/inspections/analyses of the rudder servo actuators,
and related investigative/corrective actions if necessary. Since we
issued AD 2005-17-14, analyses of the inspection results indicated that
the assumptions made to establish the survey campaign were not
adequate, and a new investigation determined the existing inspection
procedures and compliance times do not adequately address the unsafe
condition. This proposed AD would retain some requirements of AD 2005-
17-14 and revise the inspection procedures and compliance times, as
specified in an European Aviation Safety Agency (EASA) AD, which will
be incorporated by reference. We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on this proposed AD by July 25, 2019.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For the incorporation by reference (IBR) material described in the
``Related IBR material under 1 CFR part 51'' section in SUPPLEMENTARY
INFORMATION, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 89990 1000; email [email protected];
internet www.easa.europa.eu. You may find this IBR material on the EASA
website at https://ad.easa.europa.eu. You may view this IBR material at
the FAA, Transport Standards 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 in the AD docket on the
internet at https://www.regulations.gov.
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-2019-
0402; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (telephone 800-
647-5527) is listed above. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2019-0402;
Product Identifier 2019-NM-008-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM based on
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this NPRM.
Discussion
We issued AD 2005-17-14, Amendment 39-14235 (70 FR 50157, August
26, 2005) (``AD 2005-17-14''), for all Airbus SAS Model A300 series
airplanes, Model A300-600 series airplanes, and Model A310 series
airplanes. AD 2005-17-14 requires repetitive tests to detect
desynchronization of the rudder servo actuators, and adjustment or
replacement of the spring rods of the rudder servo actuators, if
necessary; and repetitive tests, inspections, and analyses of the
rudder servo actuators, and related investigative and corrective
actions if necessary. AD 2005-17-14 resulted from new reports of
desynchronization of the rudder servo actuators. We issued AD 2005-17-
14 to address desynchronization of one of the three rudder servo
actuators, which, if combined with an engine failure, could result in
the loss of the related hydraulic system and could cause the loss of
one of the two synchronized actuators. This condition could create
additional fatigue loading and possible cracking of the attachment
fittings and could result in the inability of the remaining
synchronized actuator to maintain the commanded rudder deflection,
leading to reduced controllability of the airplane.
Actions Since AD 2005-17-14 Was Issued
Since we issued AD 2005-17-14, EASA reported that analyses of the
inspection results indicate that the assumptions made in 2004 to
establish the survey campaign were not adequate. This determination led
to investigation and revision of the service information with revised
inspection instructions and compliance times, depending on airplane
configuration.
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2019-0017, dated January 29, 2019
(``EASA AD 2019-0017'') (also referred to as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for all Airbus SAS Model A300 series airplanes, Model A300-
600 series airplanes, and Model A310 series airplanes. The MCAI states:
Numerous occurrences were reported of rudder servo control de-
synchronization, some of which had caused structural damages to the
fin or side fittings of the rudder actuator attachments. Analyses
revealed that a de-synchronization of the rudder servo control
induced by misalignment of the three servo controls, or by thermal
expansion, can provoke opposing loads.
This condition, if not detected and corrected, could induce
failure of rudder-associated systems, possibly resulting in reduced
control of the aeroplane.
Previously, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France issued AD F-2004-063 for A300-600ST aeroplanes, and
AD F-2004-092 (EASA approval 2004-6368) [which corresponds to FAA AD
2005-17-14] for A300, A310 and A300-600 aeroplanes, to require
repetitive inspections of rudder servo controls, fin box and rudder
structures, and, depending on findings, accomplishment of applicable
corrective action(s).
Since those ADs were issued, analyses of the inspection results
indicate that the assumptions made in 2004 to establish the survey
campaign were not adequate. This determination induced new
investigation and ATA 55 SBs [service bulletins] revision with new
inspection instructions and new
[[Page 26783]]
compliance times, depending on aeroplane configuration.
For the reason described above, this [EASA] AD retains partially
the requirements of DGAC France AD F-2004-063 and AD F-2004-092
(EASA approval 2004-6368), which are superseded, and requires the
new inspections (latest SB revision) at new intervals.
The new repetitive intervals for the inspections specified in
paragraph (2) of EASA AD 2019-0017 range from 300 flight cycles to
6,000 flight cycles, depending on inspection type.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2005-17-14, this proposed AD would retain certain
requirements of AD 2005-17-14. Those requirements are referenced in
EASA AD 2019-0017, which, in turn, is referenced in paragraph (g) of
this proposed AD.
Related IBR Material Under 1 CFR Part 51
EASA AD 2019-0017 describes procedures for repetitive inspections
of the rudder servo actuators and related investigative/corrective
actions. Related investigative actions include repetitive inspections
of fin box and rudder servo controls. Corrective actions include
repair. This material 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 and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI referenced
above. We are proposing this AD because we evaluated all pertinent
information and determined an unsafe condition exists and is likely to
exist or develop on other products of the same type design.
Proposed Requirements of This NPRM
This proposed AD would require accomplishing the actions specified
in EASA AD 2019-0017 described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this AD and except as discussed under ``Differences
Between this Proposed AD and the MCAI.''
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA worked with Airbus and EASA to develop a process to
use certain EASA ADs as the primary source of information for
compliance with requirements for corresponding FAA ADs. As a result,
EASA AD 2019-0017 will be incorporated by reference in the FAA final
rule. This proposed AD would, therefore, require compliance with the
provisions specified in EASA AD 2019-0017, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
Service information specified in EASA AD 2019-0017 that is required for
compliance with EASA AD 2019-0017 will be available on the internet
https://www.regulations.gov by searching for and locating Docket No.
FAA-2019-0402 after the FAA final rule is published.
Differences Between This Proposed AD and the MCAI
Where paragraph (4) of EASA AD 2019-0017 refers to ``during any
inspection as required by paragraph (2) of this AD,'' this proposed AD
would require using ``during any inspection as required by paragraph
(2) or (3) of this AD.'' EASA AD 2019-0017 did not specify a corrective
action for the inspections required by paragraph (3) of EASA AD 2019-
0017.
Costs of Compliance
We estimate that this proposed AD affects 133 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2005-17-14... 1 work-hour x $85 per $0 $85 $11,305
hour = $85.
New proposed actions.................. 2 work-hours x $85 per 0 170 22,610
hour = $85.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.
We estimate that it would take about 1 work-hour per product to
comply with the proposed reporting requirement in this proposed AD. The
average labor rate is $85 per hour. Based on these figures, we estimate
the cost of reporting the inspection results on U.S. operators to be
$11,305, or $85 per product.
We estimate the following costs to do any necessary on-condition
inspections that would be required based on the results of any required
actions. We have no way of determining the number of aircraft that
might need these on-condition actions:
Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
34 work-hours x $85 per hour = $2,890. $0 $2,890
------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repair specified in this proposed
AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this NPRM is 2120-
0056. The paperwork cost associated with this NPRM has been detailed in
the Costs of
[[Page 26784]]
Compliance section of this document and includes time for reviewing
instructions, as well as completing and reviewing the collection of
information. Therefore, all reporting associated with this NPRM is
mandatory. Comments concerning the accuracy of this burden and
suggestions for reducing the burden should be directed to the FAA at
800 Independence Ave. SW, Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the 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 this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2005-17-14, Amendment 39-14235 (70 FR 50157, August 26, 2005), and
adding the following new AD:
Airbus SAS: Docket No. FAA-2019-0402; Product Identifier 2019-NM-
008-AD.
(a) Comments Due Date
We must receive comments by July 25, 2019.
(b) Affected ADs
This AD replaces AD 2005-17-14, Amendment 39-14235 (70 FR 50157,
August 26, 2005) (``AD 2005-17-14'').
(c) Applicability
This AD applies to the Airbus SAS airplanes, certificated in any
category, specified in paragraphs (c)(1) through (c)(3) of this AD,
as identified in European Aviation Safety Agency (EASA) AD 2019-
0017, dated January 29, 2019 (``EASA AD 2019-0017'').
(1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R,
F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F
airplanes.
(3) Model A310-203, -204, -221, -222, -304, -322, -324, and -325
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls; 55, Stabilizers.
(e) Reason
This AD was prompted by reports of desynchronization of the
rudder servo actuators. We are issuing this AD to address
desynchronization of one of the three rudder servo actuators, which,
if combined with an engine failure, could result in the loss of the
related hydraulic system and could cause the loss of one of the two
synchronized actuators. This condition could create additional
fatigue loading and possible cracking of the attachment fittings and
could result in the inability of the remaining synchronized actuator
to maintain the commanded rudder deflection, leading to reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2019-0017.
(h) Exceptions to EASA AD 2019-0017
(1) For purposes of determining compliance with the requirements
of this AD: Where EASA AD 2019-0017 refers to its effective date,
this AD requires using the effective date of this AD.
(2) For purposes of determining compliance with the requirements
of this AD: Where paragraph (1) of EASA AD 2019-0017 specifies
``after the last inspection as previously required by DGAC France AD
F-2004-092,'' this AD requires using ``after the most recent
inspection done as specified in Airbus Service Bulletin A300-27-
0188, Revision 2, dated October 1, 1997; A300-27-6036, Revision 2,
dated October 1, 1997; A300-55-0044, dated October 22, 1996; A300-
55-6023, dated October 22, 1996; A310-27-2082, Revision 2, dated
October 1, 1997; or A310-55-2026, dated October 22, 1996.''
(3) For purposes of determining compliance with the requirements
of this AD: Where paragraph (1) of EASA AD 2019-0017 refers to ``the
03 July 2004,'' this AD requires using ``September 30, 2005'' (the
effective date of AD 2005-17-14).
(4) For purposes of determining compliance with the requirements
of this AD: Where paragraph (4) of EASA AD 2019-0017 refers to
``during any inspection as required by paragraph (2) of this AD,''
this AD requires using ``during any inspection as required by
paragraph (2) or (3) of this AD.''
(5) Where any service information referenced in EASA AD 2019-
0017 specifies reporting, this AD requires reporting all inspection
results at the applicable time specified in paragraph (h)(5)(i) or
(h)(5)(ii) of this AD. If operators have reported findings as part
of obtaining any corrective actions approved by Airbus SAS's EASA
Design Organization Approval (DOA), operators are not required to
report those findings as specified in this paragraph.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
[[Page 26785]]
(6) The ``Remarks'' section of EASA AD 2019-0017 does not apply
to this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards 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 International Section, send it to the attention of
the person identified in paragraph (j)(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 local flight
standards district office/certificate holding district 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, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's
EASA Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): For any service information
referenced in EASA AD 2019-0017 that contains RC procedures and
tests: Except as required by paragraph (i)(2) of this AD, RC
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.
(4) Paperwork Reduction Act Burden Statement: A federal agency
may not conduct or sponsor, and a person is not required to respond
to, nor shall a person be subject to a penalty for failure to comply
with a collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 1
hour per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW, Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(j) Related Information
(1) For information about EASA AD 2019-0017, contact the EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
89990 6017; email [email protected]; Internet www.easa.europa.eu.
You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. You may view this EASA AD at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195. EASA AD 2019-0017 may be found in the AD docket on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0402.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3225.
Issued in Des Moines, Washington, on May 28, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-11896 Filed 6-7-19; 8:45 am]
BILLING CODE 4910-13-P
