Airworthiness Directives; Airbus SAS Airplanes, 30579-30588 [2019-13545]
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Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 adding
the following new airworthiness
directive (AD):
■
2019–12–13 The Boeing Company:
Amendment 39–19668; Docket No.
FAA–2019–0445; Product Identifier
2019–NM–083–AD.
(a) Effective Date
This AD is effective July 12, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 757–200, –200PF, –200CB,
and –300 series airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Unsafe Condition
This AD was prompted by a report of the
failure of the aileron trim actuator attachment
lug. The FAA is issuing this AD to address
failure of the aileron trim actuator attachment
lug and subsequent loss of feel force, wheel
centering, and lateral trim. This condition, if
not corrected, could cause over-control of the
airplane and subsequent lateral pilot induced
oscillations (PIO), which could adversely
affect continued safe flight and landing.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
Except as specified by paragraph (h) of this
AD: At the applicable times specified in the
‘‘Compliance’’ paragraph of Boeing Alert
Requirements Bulletin 757–27A0159 RB,
dated March 29, 2019, do all applicable
actions identified in, and in accordance with,
the Accomplishment Instructions of Boeing
Alert Requirements Bulletin 757–27A0159
RB, dated March 29, 2019.
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Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 757–27A0159, dated March 29,
2019, which is referred to in Boeing Alert
Requirements Bulletin 757–27A0159 RB,
dated March 29, 2019.
(h) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Alert Requirements Bulletin
757–27A0159 RB, dated March 29, 2019, uses
the phrase ‘‘the original issue date of the
Requirements Bulletin 757–27A0159 RB,’’
this AD requires using ‘‘the effective date of
this AD.’’
(2) Where Boeing Alert Requirements
Bulletin 757–27A0159 RB, dated March 29,
2019, specifies contacting Boeing for repair
instructions: This AD requires doing the
repair using a method approved in
accordance with the procedures specified in
paragraph (i) of this AD.
(i) 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 (j) of this
AD. Information may be emailed to: 9-ANMLAACO-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.
(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 Company
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.
(j) Related Information
For more information about this AD,
contact Katherine Venegas, Aerospace
Engineer, Cabin Safety and Environmental
Systems Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5353; fax: 562–627–5210; email:
katherine.venegas@faa.gov.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
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(i) Boeing Alert Requirements Bulletin
757–27A0159 RB, dated March 29, 2019.
(ii) [Reserved]
(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;
telephone 562–797–1717; internet https://
www.myboeingfleet.com.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on June
18, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–13514 Filed 6–26–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0017; Product
Identifier 2018–NM–112–AD; Amendment
39–19662; AD 2019–12–07]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2007–11–
11 and AD 2017–01–11, which applied
to all Airbus SAS Model A318 and
Model A319 series airplanes; Model
A320–211, –212, –214, –231, –232, and
–233 airplanes; and Model A321 series
airplanes. AD 2007–11–11 required an
inspection to determine the serial
number of both main landing gear
(MLG) sliding tubes, repetitive
inspections for cracking of the affected
MLG sliding tubes and corrective
actions if necessary, and eventual
replacement of both MLG shock
absorbers. AD 2017–01–11 required
identification of the part number and
serial number of the MLG sliding tubes;
inspection of affected chromium plates
and sliding tube axles for damage; and
replacement of the sliding tube if
SUMMARY:
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Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations
necessary. This AD retains certain
requirements of AD 2007–11–11 and AD
2017–01–11. This AD also requires
repetitive inspections of affected MLG
sliding tubes for cracking, replacement
of cracked MLG sliding tubes, and
eventual replacement of each affected
MLG sliding tube. This AD was
prompted by cracks found in the MLG
sliding tubes due to certain
manufacturing defects that might not be
identified using the current on-wing
scheduled inspections. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 1,
2019.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 1, 2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of February 22, 2017 (82 FR
5362, January 18, 2017).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of June 29, 2007 (72 FR
29241, May 25, 2007).
ADDRESSES: For Airbus service
information identified in this final rule,
contact Airbus SAS, Airworthiness
Office—EIAS, Rond-Point Emile
Dewoitine No: 2, 31700 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
internet https://www.airbus.com.
For Safran and Messier-Dowty service
information identified in this final rule,
contact Safran Landing Systems, One
Carbon Way, Walton, KY 41094;
telephone (859) 525–8583; fax (859)
485–8827; internet https://www.safranlanding-systems.com.
You may view this referenced 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. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0017.
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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–
0017; 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,
the regulatory evaluation, any
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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:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2007–11–11,
Amendment 39–15068 (72 FR 29241,
May 25, 2007) (‘‘AD 2007–11–11’’), and
AD 2017–01–11, Amendment 39–18778
(82 FR 5362, January 18, 2017) (‘‘AD
2017–01–11’’). AD 2007–11–11 applied
to all Airbus SAS Model A318 and
Model A319 series airplanes; Model
A320–211, –212, –214, –231, –232, and
–233 airplanes; and Model A321 series
airplanes. AD 2017–01–11 applied to all
Airbus SAS Model A318 and Model
A319 series airplanes; Model A320–211,
–212, –214, –231, –232, and –233
airplanes; and Model A321 series
airplanes.
The NPRM published in the Federal
Register on February 25, 2019 (84 FR
5960). The NPRM was prompted by a
determination that cracks were found in
the MLG sliding tubes due to certain
manufacturing defects that might not be
identified using the current on-wing
scheduled inspections. The NPRM
proposed to retain certain requirements
of AD 2007–11–11 and AD 2017–01–11.
The NPRM also proposed to require
repetitive inspections of affected MLG
sliding tubes for cracking, replacement
of cracked MLG sliding tubes, and
eventual replacement of each affected
MLG sliding tube. The FAA is issuing
this AD to address cracking in an MLG
sliding tube, which could lead to failure
of an MLG sliding tube resulting in MLG
collapse, damage to the airplane, and
injury to passengers.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0135,
dated June 26, 2018 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus SAS Model A318 and
A319 series airplanes; Model A320–211,
–212, –214, –216, –231, –232, and –233
airplanes; and Model A321–111, –112,
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–131, –211, –212, –213, –231, and –232
airplanes. The MCAI states:
Cracks were reported on [main landing
gear] MLG sliding tubes and the
investigations determined metallic inclusion
during production and abnormal grinding
operation during overhaul as cause of these
cracks. Prompted by these reports,
respectively, [Direction Generale de
l’Aviation Civile] DGAC France issued
[French] AD F–2005–115 (EASA approval
2005–6032) [which corresponds to FAA AD
2007–11–11] and EASA issued AD 2014–
0058 [which corresponds to FAA AD 2017–
01–11], both requiring inspections and
replacement of certain MLG sliding tubes.
More recently, during overhaul, cracks
were found in the lower slave link bracket
lug holes on two MLG sliding tubes.
Subsequent investigations determined that
these cracks may have developed due to
burrs, which could have been present since
manufacture. Based on the fact that the
sliding tube is certified as a safe life part, this
is considered to be a non-compliance with
the requirements of [Joint Aviation
Requirements] JAR 25.571(c). Cracks in the
affected sliding tubes may not be found
during the existing on-wing scheduled
inspections.
This condition, if not detected and
corrected, could lead to sliding tube failure,
possibly resulting in MLG collapse, damage
to the aeroplane and injury to occupants.
Prompted by these findings, Safran
Landing Systems, the MLG manufacturer
(formerly Messier-Dowty, Messier-BugattiDowty, and hereafter referred to as ‘‘Safran’’
in this AD), introduced additional quality
steps to eliminate burrs in the manufacturing
process. To address this potential unsafe
condition on delivered MLG sliding tubes,
Airbus issued SB [service bulletin] A320–32–
1441, providing instructions for on-wing
repetitive inspections, and Safran issued SB
200–32–321 and SB 201–32–68, as applicable
to MLG configuration, providing instructions
for inspection in shop.
For the reason described above, this
[EASA] AD partially retains the requirements
of DGAC France AD F–2005–115 (EASA
approval 2005–6032) and EASA AD 2014–
0058, which are superseded, requires
repetitive inspections of the affected MLG
sliding tubes [for cracking] and, depending
on findings, accomplishment of applicable
corrective action(s) [replacement of a cracked
MLG sliding tube with a serviceable MLG
sliding tube]. This [EASA] AD also defines
criteria for installation on an aeroplane of an
affected MLG sliding tube.
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–2019–
0017.
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The following presents
the comments received on the NPRM
and the FAA’s response to each
comment.
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Support for the NPRM
Air Line Pilots Association,
International (ALPA) supported the
intent of the NPRM.
Request To Remove Functional Testing
From ‘‘Required for Compliance (RC)’’
Requirements
Delta Air Lines (DAL) requested that
the functional testing requirement be
removed from the required for
compliance ‘‘RC’’ procedures identified
in the Accomplishment Instructions of
Airbus Service Bulletin A320–32–1441,
Revision 01, dated December 14, 2017.
The commenter explained that
paragraph 3.D. of the Accomplishment
Instructions of Airbus Service Bulletin
A320–32–1441, Revision 01, dated
December 14, 2017, describes postmodification testing, which results in
functional testing of the brake and
wheel installation functionality. The
commenter noted that these tests do not
require any special equipment for
testing or require the operation of
equipment. The commenter stated that
it would prefer to use the airplane
maintenance manual (AMM) procedures
instead of a functional test.
The FAA disagrees with the
commenter’s request. Functional testing
is required by EASA, the state of design
authority for the Model A318 and Model
A319 series airplanes; Model A320–211,
–212, –214, –231, –232, and –233
airplanes; and Model A321 series
airplanes; to restore the airplane to its
type design requirements. In addition,
the functional test procedure described
in the above mentioned Airbus service
information refers to the procedures in
AMM task 32–41–11–400–006,
‘‘Installation of the MLG Wheels,’’ to
perform the functional test, which is
what the commenter requested. The
functional test is required for
compliance to ensure that risk has been
mitigated and the airplane can be
returned to service per the type design
requirements. The FAA has not changed
this AD in regard to this issue.
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Request for Clarification of Definition
DAL observed that paragraph (n)(1) of
the proposed AD defined affected MLG
shock absorbers as those having a part
number and serial number identified in
Messier-Dowty Service Bulletin 200–
32–286, Revision 3, dated October 3,
2008, for Model A318, A319, and A320
series airplanes; and Messier-Dowty
Service Bulletin 201–32–43, Revision 3,
dated October 3, 2008, for Model A321
series airplanes. DAL noted that, upon
review of this service information, it
determined that there are no specific
part number and serial number
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combinations for the MLG shock
absorbers listed, and that the service
information identified serial numbers
for only the MLG sliding tubes.
From these statements, the FAA infers
that DAL was requesting clarification of
the definition of an affected MLG shock
absorber. The FAA agrees to clarify this
definition. An affected MLG shock
absorber assembly contains an affected
MLG sliding tube subassembly. The
intent of paragraph (n) of this AD is to
assist operators in identification of the
discrepant MLG sliding tube part
numbers. Furthermore, this definition
matches what was provided in the
corresponding MCAI AD issued by
EASA. The FAA has not revised this AD
in regard to this issue.
Request for Clarification of Parts
Installation Prohibition
DAL requested that paragraph (r)(1) of
the proposed AD be revised to state that,
as of the effective date of the AD, no
person may install an affected MLG
sliding tube on any airplane. The
commenter noted that paragraph (r)(1)
of the proposed AD stated that, as of the
effective date of this AD, no person may
install on any airplane an affected MLG
shock absorber. The commenter stated
that its request is supported by the fact
that the proposed AD only described
inspections and actions based on the
MLG sliding tubes, not the remainder of
the MLG shock absorber. The
commenter further explained that it is
feasible that non-sliding tube
components of the MLG shock absorber
assemblies may be perfectly fit for
operation beyond the AD replacement
times. The commenter observed that
this change would allow operators to
use any existing stock of MLG shock
absorber related components (other than
the affected MLG sliding tubes). The
commenter stated that its position is
further supported by the statements in
the ‘‘Proposed Requirements of this
NPRM’’ paragraph, because no mention
of an MLG shock absorber replacement
is discussed. The commenter also
explained that it would be difficult to
comply with the proposed requirement
specified in paragraph (r)(1) of the
proposed AD, since paragraph (n)(2) of
the proposed AD does not list specific
MLG shock absorber part number and
serial number combinations.
The FAA agrees with the intent of the
commenter’s request. The affected MLG
shock absorber assembly contains an
MLG sliding tube subassembly. The
intent of paragraph (r)(1) of this AD is
to prohibit the installation of an MLG
shock absorber assembly containing a
discrepant MLG sliding tube
subassembly part number. The FAA has
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30581
revised paragraph (r)(1) of this AD to
prohibit, as of the effective date of this
AD, the installation of an MLG shock
absorber assembly containing a
discrepant MLG sliding tube part
number.
Request To Allow the Use of Future
Revisions of Service Information
DAL requested that the proposed AD
be revised to allow the use of future
revisions of the service information. The
commenter noted that the EASA AD
allows the use of future revisions of
service information.
The FAA disagrees with the
commenter’s request. The FAA may not
refer to any document that does not yet
exist. In general terms, the FAA is
required by Office of the Federal
Register (OFR) regulations for approval
of materials incorporated by reference,
as specified in 1 CFR 51.1(f), to either
publish the service document contents
as part of the actual AD language; or
submit the service document to the OFR
for approval as referenced material, in
which case the FAA may only refer to
such material in the text of an AD. The
AD may refer to the service document
only if the OFR approved it for
incorporation by reference. See 1 CFR
part 51. To allow operators to use later
revisions of the referenced document
(issued after publication of the AD),
either the FAA must revise the AD to
reference specific later revisions, or
operators must request approval to use
later revisions as an alternative method
of compliance with this AD under the
provisions of paragraph (w)(1) of this
AD. The FAA has not revised this AD
regarding this issue.
Conclusion
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the changes described
previously and 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.
The FAA also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
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• Service Bulletin A320–32–1441,
Revision 01, dated December 14, 2017.
This service information describes
procedures for inspections of the MLG
sliding tubes for cracking and corrective
actions (which includes replacing the
MLG sliding tubes).
• Service Bulletin A320–32A1273,
Revision 02, dated May 26, 2005. This
service information specifies the serial
numbers of the MLG sliding tubes that
must be replaced.
Safran Landing Systems has issued
the following service information. These
documents are distinct since they apply
to different airplane models.
• Safran Service Bulletin 200–32–
321, Revision 2, dated October 3, 2017;
and Service Bulletin 201–32–68,
Revision 2, dated October 3, 2017.
These documents specify the part
numbers and serial numbers of the
affected MLG sliding tubes.
• Messier-Dowty Service Bulletin
200–32–286, Revision 3, dated October
3, 2008; and Service Bulletin 201–32–
43, Revision 3, dated October 3, 2008.
These documents specify the part
numbers and serial numbers of the
affected MLG shock absorbers.
This AD also requires Airbus Service
Bulletin A320–32–1416, including
Appendix 01, dated March 10, 2014,
which the Director of the Federal
Register approved for incorporation by
reference as of February 22, 2017 (82 FR
5362, January 18, 2017).
This AD also requires Airbus Service
Bulletin A320–32A1273, Revision 02,
including Appendix 01, dated May 26,
2005, which the Director of the Federal
Register approved for incorporation by
reference as of June 29, 2007 (72 FR
29241, May 25, 2007).
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD
affects 1,186 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
Retained actions from AD 2007–11–11
(297 airplanes) *.
Retained actions from AD 2017–01–11 ..
New actions .............................................
8 work-hours × $85 per hour = $680 ......
Up to $45,310 ..
Up to $46,670 ..
Up to $13,659,030.*
18 work-hours × $85 per hour = $1,530
13 work-hours × $85 per hour = $1,105
$0 .....................
(**) ...................
$1,530 ..............
$1,105 ** ..........
$1,814,580.
$1,310,530.**
* Operators should note that, although all U.S.-registered airplanes are subject to the requirements of AD 2007–11–11, there are only 297 possible affected MLG sliding tubes in the worldwide fleet. The FAA has no way of knowing how many affected MLG sliding tubes, if any, are installed in U.S.-registered airplanes.
** The FAA has received no definitive data for the parts costs for the replacements.
The FAA estimates the following
costs to do any necessary on-condition
action that would be required based on
the results of any required actions. The
FAA has no way of determining the
number of aircraft that might need this
on-condition action:
ESTIMATED COSTS OF ON-CONDITION ACTION
Labor cost
Parts cost
Cost per
product
6 work-hours × $85 per hour = $510 ......................................................................................................................
(*)
* $510
* The FAA has received no definitive data for the parts costs for the on-condition actions.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: ‘‘General requirements.’’ Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
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develop on products identified in this
rulemaking action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes and associated appliances to
the Director of the System Oversight
Division.
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
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between the national government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Will not affect intrastate aviation in
Alaska; and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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(3) Model A320–211, –212, –214, –216,
–231, –232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing gear.
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) 2007–11–11, Amendment 39–
15068 (72 FR 29241, May 25, 2007); and
AD 2017–01–11, Amendment 39–18778
(82 FR 5362, January 18, 2017);
■ b. Adding the following new AD:
■
■
2019–12–07 Airbus SAS: Amendment 39–
19662; Docket No. FAA–2019–0017;
Product Identifier 2018–NM–112–AD.
(a) Effective Date
This AD is effective August 1, 2019.
(b) Affected ADs
This AD replaces the following ADs.
(1) AD 2007–11–11, Amendment 39–15068
(72 FR 29241, May 25, 2007) (‘‘AD 2007–11–
11’’).
(2) AD 2017–01–11, Amendment 39–18778
(82 FR 5362, January 18, 2017) (‘‘AD 2017–
01–11’’).
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(c) Applicability
This AD applies to the Airbus SAS
airplanes identified in paragraphs (c)(1)
through (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers
(MSNs).
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
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(e) Reason
This AD was prompted by a determination
that cracks were found in the main landing
gear (MLG) sliding tubes due to certain
manufacturing defects that might not be
identified using the current on-wing
scheduled inspections. The FAA is issuing
this AD to address cracking in an MLG
sliding tube, which could lead to failure of
an MLG sliding tube resulting in MLG
collapse, damage to the airplane, and injury
to passengers.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Replacement of AD 2007–11–11,
With Updated References to Service
Information and Specific Delegation
Approval Language
This paragraph restates the requirements of
paragraph (i) of AD 2007–11–11, with
updated references to service information
and specific delegation approval language.
Within 41 months after June 29, 2007 (the
effective date of AD 2007–11–11), replace all
MLG shock absorbers equipped with MLG
sliding tubes having serial numbers listed in
Airbus All Operators Telex (AOT) A320–
32A1273, Revision 01, dated May 6, 2004; or
the Accomplishment Instructions of Airbus
Service Bulletin A320–32A1273, Revision 02,
including Appendix 01, dated May 26, 2005;
with new or serviceable MLG shock
absorbers equipped with MLG sliding tubes
having serial numbers not listed in Airbus
AOT A320–32A1273, Revision 01, dated May
6, 2004; or the Accomplishment Instructions
of Airbus Service Bulletin A320–32A1273,
Revision 02, including Appendix 01, dated
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May 26, 2005; using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the European
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.
As of June 29, 2007, only Airbus Service
Bulletin A320–32A1273, Revision 02,
including Appendix 01, dated May 26, 2005,
may be used to determine the affected MLG
sliding tubes.
Note 1 to paragraph (g): Guidance on the
replacement specified in paragraph (g) of this
AD can be found in Airbus A318/A319/
A320/A321 Aircraft Maintenance Manual
Chapter 32–11–13, page block 401.
(h) Retained MLG Sliding Tube Part Number
and Serial Number Identification of AD
2017–01–11, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2017–01–11, with no
changes. Within three months after February
22, 2017 (the effective date of AD 2017–01–
11): Do an inspection to identify the part
number and serial number of the MLG
sliding tubes installed on the airplane. A
review of airplane maintenance records is
acceptable in lieu of this inspection if the
part number and serial number of the MLG
sliding tubes can be conclusively determined
from that review.
(i) Retained Identification of Airplanes of
AD 2017–01–11, With No Changes
This paragraph restates the identification
specified in paragraph (h) of AD 2017–01–11,
with no changes. An airplane with a MSN
not listed in figure 1 to paragraph (i) of this
AD is not affected by the requirements of
paragraph (j) of this AD, provided it can be
determined that no MLG sliding tube having
a part number and serial number listed in
table 1 to paragraphs (i), (j), (l)(1), (l)(2),
(m)(1), and (m)(2) of this AD has been
installed on that airplane since first flight of
the airplane.
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Figure 1 to Paragraph (i) -Affected Airplanes Listed by MSN
Affected Airplanes Listed by MSN
0179
0214
0296
0412
0558
0604
0607
0668
0704
0720
0726
0731
0754
0771
0799
0828
0841
0855
0909
0914
0925
0939
0986
1028
1030
1041
1070
1083
1093
1098
1108
1148
1294
1356
2713
2831
Serial Number
201160302
788
201160302
1016811
201160302
11448
201371302
84493
201371302
84513
201371302
SS4359
201371302
84530
201371302
84517
201371302
84568
201371302
84498
201371302
44908
201371302
8202-4598
201371302
8165-4623
201371302
8244-4766
201371302
8267-4794
201371302
8272-4813
201160302
11088
ER27JN19.001</GPH>
Part Number
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Table 1 to Paragraphs (i), (j), (1)(1), (1)(2), (m)(1), and (m)(2)- Affected MLG Sliding
Tubes
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Part Number
Serial Number
201371304
B041-4871
201371304
B045-4869
201371304
B001-4781
201371304
B051-4892
201371304
B110-1952
201371304
B054-4891
201371304
B063-4921
201371304
B071-4911
201371304
B071-4917
201371304
B080-1933
201371304
B117-5010
201371304
B120-4989
201371304
B132-2023
201371304
B114-1956
201371304
B208-2009
201371304
B133-1947
201371304
B154-5037
201371304
B89 4952
201371304
B129-1964
201371304
B227-2010
201371304
B170-5031
201371304
B182-5047
201371304
B239-2053
201371304
201371304
B1401-2856
B1813-3142
201371304
B116-5004
201522353
B011-149
201522350
B014-25
201522350
B019-56
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BILLING CODE 4910–13–C
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(j) Retained Inspections of AD 2017–01–11,
With No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2017–01–11, with no
changes. For each MLG sliding tube
identified as required by paragraph (h) of this
AD, having a part number and serial number
listed in table 1 to paragraphs (i), (j), (l)(1),
(l)(2), (m)(1), and (m)(2) of this AD: Within
3 months after February 22, 2017 (the
effective date of AD 2017–01–11) inspect
affected MLG axles and brake flanges by
doing a detailed visual inspection of the
chromium plates for damage, and a
Barkhausen noise inspection of the MLG
sliding tube axles for damage, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–32–1416,
including Appendix 01, dated March 10,
2014. For Model A318 series airplanes, use
the procedures specified for Model A319
series airplanes in Airbus Service Bulletin
A320–32–1416, including Appendix 01,
dated March 10, 2014.
(k) Retained Corrective Action of AD 2017–
01–11, With No Changes
This paragraph restates the requirements of
paragraph (j) of AD 2017–01–11, with no
changes. If, during any inspection required
by paragraph (j) of this AD, any damage is
detected: Before further flight, replace the
MLG sliding tube with a serviceable MLG
sliding tube, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1416, including
Appendix 01, dated March 10, 2014. For
Model A318 series airplanes, use the
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procedures specified for Model A319 series
airplanes in Airbus Service Bulletin A320–
32–1416, including Appendix 01, dated
March 10, 2014.
(l) Retained Definition of Serviceable MLG
Sliding Tube of AD 2017–01–11, With No
Changes
This paragraph restates the definition
specified in paragraph (k) of AD 2017–01–11,
with no changes. For the purpose of
paragraph (k) of this AD, a serviceable MLG
sliding tube is defined as an MLG sliding
tube that meets the criterion in either
paragraph (l)(1) or (l)(2) of this AD.
(1) An MLG sliding tube having a part
number and serial number not listed in table
1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and
(m)(2) of this AD.
(2) An MLG sliding tube having a part
number and serial number listed in table 1
to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and
(m)(2) of this AD that has passed the
inspections required by paragraph (j) of this
AD.
(m) Retained Parts Installation Prohibition
of AD 2017–01–11, With No Changes
This paragraph restates the requirements of
paragraph (l) of AD 2017–01–11, with no
changes.
(1) For airplanes that have an MLG sliding
tube installed that has a part number and
serial number listed in table 1 to paragraphs
(i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this
AD: After an airplane is returned to service
following accomplishment of the actions
required by paragraphs (h), (i), and (j) of this
AD, no person may install on any airplane an
MLG sliding tube having a part number and
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serial number listed in table 1 to paragraphs
(i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this
AD, unless that MLG sliding tube has passed
the inspection required by paragraph (j) of
this AD.
(2) For airplanes that, as of February 22,
2017 (the effective date of AD 2017–01–11),
do not have an MLG sliding tube installed
that has a part number and serial number
listed in table 1 to paragraphs (i), (j), (l)(1),
(l)(2), (m)(1), and (m)(2) of this AD: No
person may install, on any airplane, an MLG
sliding tube having a part number and serial
number listed in table 1 to paragraphs (i), (j),
(l)(1), (l)(2), (m)(1), and (m)(2) of this AD
unless that MLG sliding tube has passed the
inspection required by paragraph (j) of this
AD.
(n) New Definitions
For the purpose of paragraphs (o), (p), (q),
(r), and (s) of this AD the following
definitions apply.
(1) Affected MLG shock absorber: An MLG
shock absorber having a part number and
serial number as identified in Messier-Dowty
Service Bulletin 200–32–286, Revision 3,
dated October 3, 2008, for Model A318,
A319, and A320 series airplanes; and
Messier-Dowty Service Bulletin 201–32–43,
Revision 3, dated October 3, 2008, for Model
A321 series airplanes.
(2) Affected MLG sliding tube: An MLG
sliding tube having a part number and serial
number as identified in Appendix B of Safran
Service Bulletin 200–32–321, Revision 2,
dated October 3, 2017, for Model A318,
A319, and A320 series airplanes; or Safran
Service Bulletin 201–32–68, Revision 2,
dated October 3, 2017, for Model A321 series
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airplanes, except those parts that passed an
inspection as specified in Safran Service
Bulletin 200–32–321; or Safran Service
Bulletin 201–32–68; as applicable; and those
parts that, after that inspection, have been
repaired, using instructions approved by the
Manager, International Section, Transport
Standards Branch, FAA; or EASA; or Airbus
SAS’s EASA DOA. If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Serviceable MLG sliding tube: An MLG
sliding tube that is not affected, or an affected
MLG sliding tube, that has not exceeded
10,000 flight cycle since first installation on
an airplane, or an affected MLG sliding tube
that, within the last 5,000 flight cycles before
installation on an airplane, passed an
inspection specified in Airbus Service
Bulletin A320–32–1441.
(o) New Requirement of This AD: Repetitive
Inspections
Note 2 to paragraph (o): If no reliable data
regarding the number of flight cycles
accumulated by the MLG sliding tube are
available, operators may refer to the guidance
specified in Chapter 5.2, ‘‘Traceability’’, of
Section 1, of Part 1 of the Airbus A318/A319/
A320/A321 Airworthiness Limitations
Section.
(2) Do not install an affected MLG sliding
tube on any airplane as specified in
paragraph (r)(2)(i) or (r)(2)(ii) of this AD, as
applicable.
(i) For an airplane with an affected MLG
sliding tube installed as of the effective date
of this AD: After replacement of each affected
MLG sliding tube as required by paragraph
(q) of this AD.
(ii) For an airplane that does not have an
affected MLG sliding tube installed as of the
effective date of this AD: As of the effective
date of this AD.
(v) No Reporting Requirement
Although Airbus Service Bulletin A320–
32–1441, Revision 01, dated December 14,
2017, specifies to submit certain information
to the manufacturer, and specifies that action
as ‘‘RC,’’ (required for compliance) this AD
does not include that requirement.
(s) Identification of Airplanes Not Affected
by Certain Requirements of This AD
An airplane on which Airbus Modification
161202 or Modification 161346 has been
installed in production is not affected by the
requirements of paragraphs (g), (h), (j), (o),
and (q), of this AD, provided it has been
verified that no affected MLG sliding tube is
installed on that airplane.
(q) New Requirement of This AD: Part
Replacement
(1) Within 10 years after the effective date
of this AD: Replace each affected MLG
sliding tube with an MLG sliding tube that
is not affected. Installation of an MLG sliding
tube that is not affected on an airplane
constitutes terminating action for the
repetitive inspections required by paragraph
(o) of this AD for that airplane.
(2) Replacement of an MLG on an airplane
with an MLG that does not have an affected
MLG sliding tube installed is an acceptable
method to comply with the requirement of
paragraph (q)(1) of this AD for that airplane.
(t) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before June
29, 2007, using Airbus AOT A320–32A1273,
Revision 01, dated May 6, 2004. This
document was incorporated by reference in
AD 2004–11–13, Amendment 39–13659 (69
FR 31867, June 8, 2004).
(2) This paragraph provides credit for the
initial inspection and applicable corrective
actions required by paragraphs (o) and (p) of
this AD if those actions were performed
before the effective date of this AD, using the
Accomplishment Instructions in Airbus
Service Bulletin A320–32–1441, dated
December 28, 2016.
(r) New Requirement of This AD: Parts
Installation Limitation
(1) As of the effective date of this AD no
person may install on any airplane an
affected MLG shock absorber assembly
containing a discrepant MLG sliding tube
part number.
(u) Service Information Exceptions
The service information specified in
paragraph (g) of this AD has instructions to
send any cracked part to Messier-Dowty. This
AD does not include such a requirement, in
accordance with the procedures specified in
paragraph (w)(2) of this AD.
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At the compliance time specified in figure
2 to paragraph (o) of this AD, and thereafter
at intervals not to exceed 5,000 flight cycles:
Do a detailed inspection of each affected
MLG sliding tube, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1441, Revision 01,
dated December 14, 2017.
(w) Other FAA AD Provisions
(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 (x)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2007–11–11 are approved as AMOCs for the
corresponding provisions of paragraph (g) of
this AD.
(iii) AMOCs approved previously for AD
2017–01–11 are approved as AMOCs for the
corresponding provisions of paragraphs (h),
(i), (j), (k), (l), and (m) of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or EASA; or Airbus
SAS’s EASA DOA. If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): Except
as required by paragraphs (u) and (v) of this
AD: If any service information contains
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(p) New Requirement of This AD: Corrective
Actions
(1) If, during any inspection required by
paragraph (o) of this AD, any crack is
detected on an MLG sliding tube: Before
further flight, replace that MLG sliding tube
with a serviceable MLG sliding tube, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1441, Revision 01, dated December 14,
2017.
(2) Replacement of an MLG on an airplane
with an MLG having a serviceable MLG
sliding tube installed is an acceptable
method to comply with the requirements of
paragraph (p)(1) of this AD for that airplane.
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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.
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(x) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0135, dated June 26, 2018, 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–2019–0017.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (y)(6), (y)(7), and (y)(8) of this AD.
(y) 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 August 1, 2019.
(i) Airbus Service Bulletin A320–32–1441,
Revision 01, dated December 14, 2017.
(ii) Messier-Dowty Service Bulletin 200–
32–286, Revision 3, dated October 3, 2008.
(iii) Messier-Dowty Service Bulletin 201–
32–43, Revision 3, dated October 3, 2008.
(iv) Safran Service Bulletin 200–32–321,
Revision 2, dated October 3, 2017.
(v) Safran Service Bulletin 201–32–68,
Revision 2, dated October 3, 2017.
(4) The following service information was
approved for IBR on February 22, 2017 (82
FR 5362, January 18, 2017).
(i) Airbus Service Bulletin A320–32–1416,
including Appendix 01, dated March 10,
2014.
(ii) [Reserved]
(5) The following service information was
approved for IBR on June 29, 2007 (72 FR
29241, May 25, 2007).
(i) Airbus Service Bulletin A320–32A1273,
Revision 02, including Appendix 01, dated
May 26, 2005.
(ii) [Reserved]
(6) For Airbus service information
identified in this AD, contact Airbus SAS,
Airworthiness Office—EIAS, Rond-Point
Emile Dewoitine No: 2, 31700 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
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(7) For Safran and Messier-Dowty service
information identified in this AD, contact
Safran Landing Systems, One Carbon Way,
Walton, KY 41094; telephone (859) 525–
8583; fax (859) 485–8827; internet https://
www.safran-landing-systems.com.
(8) 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.
(9) 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, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on June
19, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–13545 Filed 6–26–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–1071; Product
Identifier 2018–NM–119–AD; Amendment
39–19665; AD 2019–12–10]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Fokker Services B.V. Model F28 Mark
0070 and 0100 airplanes. This AD was
prompted by a determination that new
or more restrictive airworthiness
limitations are necessary. This AD
requires revising the existing
maintenance or inspection program, as
applicable, to incorporate new or more
restrictive airworthiness limitations.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective August 1,
2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 1, 2019.
ADDRESSES: For service information
identified in this final rule, contact
Fokker Services B.V., Technical
Services Dept., P.O. Box 1357, 2130 EL
Hoofddorp, the Netherlands; telephone
SUMMARY:
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+31 (0)88–6280–350; fax +31 (0)88–
6280–111; email technicalservices@
fokker.com; internet https://
www.myfokkerfleet.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.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
1071.
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–2018–
1071; 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,
the regulatory evaluation, 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: Tom
Rodriguez, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3226.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Fokker Services B.V. Model
F28 Mark 0070 and 0100 airplanes. The
NPRM published in the Federal
Register on February 8, 2019 (84 FR
2796). The NPRM was prompted by a
determination that new or more
restrictive airworthiness limitations are
necessary. The NPRM proposed to
require revising the existing
maintenance or inspection program, as
applicable, to incorporate new or more
restrictive airworthiness limitations.
The agency is issuing this AD to address
reduced structural integrity of the
airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0159,
dated July 25, 2018 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Fokker Services B.V. Model F28
Mark 0070 and 0100 airplanes. The
MCAI states:
E:\FR\FM\27JNR1.SGM
27JNR1
]]>Agencies
[Federal Register Volume 84, Number 124 (Thursday, June 27, 2019)]
[Rules and Regulations]
[Pages 30579-30588]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-13545]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0017; Product Identifier 2018-NM-112-AD; Amendment
39-19662; AD 2019-12-07]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2007-11-11
and AD 2017-01-11, which applied to all Airbus SAS Model A318 and Model
A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233
airplanes; and Model A321 series airplanes. AD 2007-11-11 required an
inspection to determine the serial number of both main landing gear
(MLG) sliding tubes, repetitive inspections for cracking of the
affected MLG sliding tubes and corrective actions if necessary, and
eventual replacement of both MLG shock absorbers. AD 2017-01-11
required identification of the part number and serial number of the MLG
sliding tubes; inspection of affected chromium plates and sliding tube
axles for damage; and replacement of the sliding tube if
[[Page 30580]]
necessary. This AD retains certain requirements of AD 2007-11-11 and AD
2017-01-11. This AD also requires repetitive inspections of affected
MLG sliding tubes for cracking, replacement of cracked MLG sliding
tubes, and eventual replacement of each affected MLG sliding tube. This
AD was prompted by cracks found in the MLG sliding tubes due to certain
manufacturing defects that might not be identified using the current
on-wing scheduled inspections. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective August 1, 2019.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 1,
2019.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
February 22, 2017 (82 FR 5362, January 18, 2017).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of June
29, 2007 (72 FR 29241, May 25, 2007).
ADDRESSES: For Airbus service information identified in this final
rule, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email [email protected];
internet https://www.airbus.com.
For Safran and Messier-Dowty service information identified in this
final rule, contact Safran Landing Systems, One Carbon Way, Walton, KY
41094; telephone (859) 525-8583; fax (859) 485-8827; internet https://www.safran-landing-systems.com.
You may view this referenced 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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0017.
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-
0017; 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, the regulatory evaluation, 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: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2007-11-11, Amendment 39-15068 (72 FR
29241, May 25, 2007) (``AD 2007-11-11''), and AD 2017-01-11, Amendment
39-18778 (82 FR 5362, January 18, 2017) (``AD 2017-01-11''). AD 2007-
11-11 applied to all Airbus SAS Model A318 and Model A319 series
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes;
and Model A321 series airplanes. AD 2017-01-11 applied to all Airbus
SAS Model A318 and Model A319 series airplanes; Model A320-211, -212, -
214, -231, -232, and -233 airplanes; and Model A321 series airplanes.
The NPRM published in the Federal Register on February 25, 2019 (84
FR 5960). The NPRM was prompted by a determination that cracks were
found in the MLG sliding tubes due to certain manufacturing defects
that might not be identified using the current on-wing scheduled
inspections. The NPRM proposed to retain certain requirements of AD
2007-11-11 and AD 2017-01-11. The NPRM also proposed to require
repetitive inspections of affected MLG sliding tubes for cracking,
replacement of cracked MLG sliding tubes, and eventual replacement of
each affected MLG sliding tube. The FAA is issuing this AD to address
cracking in an MLG sliding tube, which could lead to failure of an MLG
sliding tube resulting in MLG collapse, damage to the airplane, and
injury to passengers.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0135, dated June 26, 2018 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus SAS Model A318 and A319 series
airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and
-232 airplanes. The MCAI states:
Cracks were reported on [main landing gear] MLG sliding tubes
and the investigations determined metallic inclusion during
production and abnormal grinding operation during overhaul as cause
of these cracks. Prompted by these reports, respectively, [Direction
Generale de l'Aviation Civile] DGAC France issued [French] AD F-
2005-115 (EASA approval 2005-6032) [which corresponds to FAA AD
2007-11-11] and EASA issued AD 2014-0058 [which corresponds to FAA
AD 2017-01-11], both requiring inspections and replacement of
certain MLG sliding tubes.
More recently, during overhaul, cracks were found in the lower
slave link bracket lug holes on two MLG sliding tubes. Subsequent
investigations determined that these cracks may have developed due
to burrs, which could have been present since manufacture. Based on
the fact that the sliding tube is certified as a safe life part,
this is considered to be a non-compliance with the requirements of
[Joint Aviation Requirements] JAR 25.571(c). Cracks in the affected
sliding tubes may not be found during the existing on-wing scheduled
inspections.
This condition, if not detected and corrected, could lead to
sliding tube failure, possibly resulting in MLG collapse, damage to
the aeroplane and injury to occupants.
Prompted by these findings, Safran Landing Systems, the MLG
manufacturer (formerly Messier-Dowty, Messier-Bugatti-Dowty, and
hereafter referred to as ``Safran'' in this AD), introduced
additional quality steps to eliminate burrs in the manufacturing
process. To address this potential unsafe condition on delivered MLG
sliding tubes, Airbus issued SB [service bulletin] A320-32-1441,
providing instructions for on-wing repetitive inspections, and
Safran issued SB 200-32-321 and SB 201-32-68, as applicable to MLG
configuration, providing instructions for inspection in shop.
For the reason described above, this [EASA] AD partially retains
the requirements of DGAC France AD F-2005-115 (EASA approval 2005-
6032) and EASA AD 2014-0058, which are superseded, requires
repetitive inspections of the affected MLG sliding tubes [for
cracking] and, depending on findings, accomplishment of applicable
corrective action(s) [replacement of a cracked MLG sliding tube with
a serviceable MLG sliding tube]. This [EASA] AD also defines
criteria for installation on an aeroplane of an affected MLG sliding
tube.
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-2019-
0017.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.
[[Page 30581]]
Support for the NPRM
Air Line Pilots Association, International (ALPA) supported the
intent of the NPRM.
Request To Remove Functional Testing From ``Required for Compliance
(RC)'' Requirements
Delta Air Lines (DAL) requested that the functional testing
requirement be removed from the required for compliance ``RC''
procedures identified in the Accomplishment Instructions of Airbus
Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
The commenter explained that paragraph 3.D. of the Accomplishment
Instructions of Airbus Service Bulletin A320-32-1441, Revision 01,
dated December 14, 2017, describes post-modification testing, which
results in functional testing of the brake and wheel installation
functionality. The commenter noted that these tests do not require any
special equipment for testing or require the operation of equipment.
The commenter stated that it would prefer to use the airplane
maintenance manual (AMM) procedures instead of a functional test.
The FAA disagrees with the commenter's request. Functional testing
is required by EASA, the state of design authority for the Model A318
and Model A319 series airplanes; Model A320-211, -212, -214, -231, -
232, and -233 airplanes; and Model A321 series airplanes; to restore
the airplane to its type design requirements. In addition, the
functional test procedure described in the above mentioned Airbus
service information refers to the procedures in AMM task 32-41-11-400-
006, ``Installation of the MLG Wheels,'' to perform the functional
test, which is what the commenter requested. The functional test is
required for compliance to ensure that risk has been mitigated and the
airplane can be returned to service per the type design requirements.
The FAA has not changed this AD in regard to this issue.
Request for Clarification of Definition
DAL observed that paragraph (n)(1) of the proposed AD defined
affected MLG shock absorbers as those having a part number and serial
number identified in Messier-Dowty Service Bulletin 200-32-286,
Revision 3, dated October 3, 2008, for Model A318, A319, and A320
series airplanes; and Messier-Dowty Service Bulletin 201-32-43,
Revision 3, dated October 3, 2008, for Model A321 series airplanes. DAL
noted that, upon review of this service information, it determined that
there are no specific part number and serial number combinations for
the MLG shock absorbers listed, and that the service information
identified serial numbers for only the MLG sliding tubes.
From these statements, the FAA infers that DAL was requesting
clarification of the definition of an affected MLG shock absorber. The
FAA agrees to clarify this definition. An affected MLG shock absorber
assembly contains an affected MLG sliding tube subassembly. The intent
of paragraph (n) of this AD is to assist operators in identification of
the discrepant MLG sliding tube part numbers. Furthermore, this
definition matches what was provided in the corresponding MCAI AD
issued by EASA. The FAA has not revised this AD in regard to this
issue.
Request for Clarification of Parts Installation Prohibition
DAL requested that paragraph (r)(1) of the proposed AD be revised
to state that, as of the effective date of the AD, no person may
install an affected MLG sliding tube on any airplane. The commenter
noted that paragraph (r)(1) of the proposed AD stated that, as of the
effective date of this AD, no person may install on any airplane an
affected MLG shock absorber. The commenter stated that its request is
supported by the fact that the proposed AD only described inspections
and actions based on the MLG sliding tubes, not the remainder of the
MLG shock absorber. The commenter further explained that it is feasible
that non-sliding tube components of the MLG shock absorber assemblies
may be perfectly fit for operation beyond the AD replacement times. The
commenter observed that this change would allow operators to use any
existing stock of MLG shock absorber related components (other than the
affected MLG sliding tubes). The commenter stated that its position is
further supported by the statements in the ``Proposed Requirements of
this NPRM'' paragraph, because no mention of an MLG shock absorber
replacement is discussed. The commenter also explained that it would be
difficult to comply with the proposed requirement specified in
paragraph (r)(1) of the proposed AD, since paragraph (n)(2) of the
proposed AD does not list specific MLG shock absorber part number and
serial number combinations.
The FAA agrees with the intent of the commenter's request. The
affected MLG shock absorber assembly contains an MLG sliding tube
subassembly. The intent of paragraph (r)(1) of this AD is to prohibit
the installation of an MLG shock absorber assembly containing a
discrepant MLG sliding tube subassembly part number. The FAA has
revised paragraph (r)(1) of this AD to prohibit, as of the effective
date of this AD, the installation of an MLG shock absorber assembly
containing a discrepant MLG sliding tube part number.
Request To Allow the Use of Future Revisions of Service Information
DAL requested that the proposed AD be revised to allow the use of
future revisions of the service information. The commenter noted that
the EASA AD allows the use of future revisions of service information.
The FAA disagrees with the commenter's request. The FAA may not
refer to any document that does not yet exist. In general terms, the
FAA is required by Office of the Federal Register (OFR) regulations for
approval of materials incorporated by reference, as specified in 1 CFR
51.1(f), to either publish the service document contents as part of the
actual AD language; or submit the service document to the OFR for
approval as referenced material, in which case the FAA may only refer
to such material in the text of an AD. The AD may refer to the service
document only if the OFR approved it for incorporation by reference.
See 1 CFR part 51. To allow operators to use later revisions of the
referenced document (issued after publication of the AD), either the
FAA must revise the AD to reference specific later revisions, or
operators must request approval to use later revisions as an
alternative method of compliance with this AD under the provisions of
paragraph (w)(1) of this AD. The FAA has not revised this AD regarding
this issue.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule with the changes described previously
and 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.
The FAA also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
[[Page 30582]]
Service Bulletin A320-32-1441, Revision 01, dated December
14, 2017. This service information describes procedures for inspections
of the MLG sliding tubes for cracking and corrective actions (which
includes replacing the MLG sliding tubes).
Service Bulletin A320-32A1273, Revision 02, dated May 26,
2005. This service information specifies the serial numbers of the MLG
sliding tubes that must be replaced.
Safran Landing Systems has issued the following service
information. These documents are distinct since they apply to different
airplane models.
Safran Service Bulletin 200-32-321, Revision 2, dated
October 3, 2017; and Service Bulletin 201-32-68, Revision 2, dated
October 3, 2017. These documents specify the part numbers and serial
numbers of the affected MLG sliding tubes.
Messier-Dowty Service Bulletin 200-32-286, Revision 3,
dated October 3, 2008; and Service Bulletin 201-32-43, Revision 3,
dated October 3, 2008. These documents specify the part numbers and
serial numbers of the affected MLG shock absorbers.
This AD also requires Airbus Service Bulletin A320-32-1416,
including Appendix 01, dated March 10, 2014, which the Director of the
Federal Register approved for incorporation by reference as of February
22, 2017 (82 FR 5362, January 18, 2017).
This AD also requires Airbus Service Bulletin A320-32A1273,
Revision 02, including Appendix 01, dated May 26, 2005, which the
Director of the Federal Register approved for incorporation by
reference as of June 29, 2007 (72 FR 29241, May 25, 2007).
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 1,186 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Retained actions from AD 2007-11-11 8 work-hours x $85 per Up to $45,310.............. Up to $46,670............. Up to $13,659,030.*
(297 airplanes) *. hour = $680.
Retained actions from AD 2017-01-11. 18 work-hours x $85 per $0......................... $1,530.................... $1,814,580.
hour = $1,530.
New actions......................... 13 work-hours x $85 per (**)....................... $1,105 **................. $1,310,530.**
hour = $1,105.
--------------------------------------------------------------------------------------------------------------------------------------------------------
* Operators should note that, although all U.S.-registered airplanes are subject to the requirements of AD 2007-11-11, there are only 297 possible
affected MLG sliding tubes in the worldwide fleet. The FAA has no way of knowing how many affected MLG sliding tubes, if any, are installed in U.S.-
registered airplanes.
** The FAA has received no definitive data for the parts costs for the replacements.
The FAA estimates the following costs to do any necessary on-
condition action that would be required based on the results of any
required actions. The FAA has no way of determining the number of
aircraft that might need this on-condition action:
Estimated Costs of On-Condition Action
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
6 work-hours x $85 per hour = $510.... (*) * $510
------------------------------------------------------------------------
* The FAA has received no definitive data for the parts costs for the on-
condition actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.
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;
2. Will not affect intrastate aviation in Alaska; and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 30583]]
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) 2007-11-11, Amendment 39-15068
(72 FR 29241, May 25, 2007); and AD 2017-01-11, Amendment 39-18778 (82
FR 5362, January 18, 2017);
0
b. Adding the following new AD:
2019-12-07 Airbus SAS: Amendment 39-19662; Docket No. FAA-2019-0017;
Product Identifier 2018-NM-112-AD.
(a) Effective Date
This AD is effective August 1, 2019.
(b) Affected ADs
This AD replaces the following ADs.
(1) AD 2007-11-11, Amendment 39-15068 (72 FR 29241, May 25,
2007) (``AD 2007-11-11'').
(2) AD 2017-01-11, Amendment 39-18778 (82 FR 5362, January 18,
2017) (``AD 2017-01-11'').
(c) Applicability
This AD applies to the Airbus SAS airplanes identified in
paragraphs (c)(1) through (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers (MSNs).
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
gear.
(e) Reason
This AD was prompted by a determination that cracks were found
in the main landing gear (MLG) sliding tubes due to certain
manufacturing defects that might not be identified using the current
on-wing scheduled inspections. The FAA is issuing this AD to address
cracking in an MLG sliding tube, which could lead to failure of an
MLG sliding tube resulting in MLG collapse, damage to the airplane,
and injury to passengers.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Replacement of AD 2007-11-11, With Updated References to
Service Information and Specific Delegation Approval Language
This paragraph restates the requirements of paragraph (i) of AD
2007-11-11, with updated references to service information and
specific delegation approval language. Within 41 months after June
29, 2007 (the effective date of AD 2007-11-11), replace all MLG
shock absorbers equipped with MLG sliding tubes having serial
numbers listed in Airbus All Operators Telex (AOT) A320-32A1273,
Revision 01, dated May 6, 2004; or the Accomplishment Instructions
of Airbus Service Bulletin A320-32A1273, Revision 02, including
Appendix 01, dated May 26, 2005; with new or serviceable MLG shock
absorbers equipped with MLG sliding tubes having serial numbers not
listed in Airbus AOT A320-32A1273, Revision 01, dated May 6, 2004;
or the Accomplishment Instructions of Airbus Service Bulletin A320-
32A1273, Revision 02, including Appendix 01, dated May 26, 2005;
using a method approved by the Manager, International Section,
Transport Standards Branch, FAA; or the European 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. As of June 29, 2007, only Airbus Service
Bulletin A320-32A1273, Revision 02, including Appendix 01, dated May
26, 2005, may be used to determine the affected MLG sliding tubes.
Note 1 to paragraph (g): Guidance on the replacement specified
in paragraph (g) of this AD can be found in Airbus A318/A319/A320/
A321 Aircraft Maintenance Manual Chapter 32-11-13, page block 401.
(h) Retained MLG Sliding Tube Part Number and Serial Number
Identification of AD 2017-01-11, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2017-01-11, with no changes. Within three months after February 22,
2017 (the effective date of AD 2017-01-11): Do an inspection to
identify the part number and serial number of the MLG sliding tubes
installed on the airplane. A review of airplane maintenance records
is acceptable in lieu of this inspection if the part number and
serial number of the MLG sliding tubes can be conclusively
determined from that review.
(i) Retained Identification of Airplanes of AD 2017-01-11, With No
Changes
This paragraph restates the identification specified in
paragraph (h) of AD 2017-01-11, with no changes. An airplane with a
MSN not listed in figure 1 to paragraph (i) of this AD is not
affected by the requirements of paragraph (j) of this AD, provided
it can be determined that no MLG sliding tube having a part number
and serial number listed in table 1 to paragraphs (i), (j), (l)(1),
(l)(2), (m)(1), and (m)(2) of this AD has been installed on that
airplane since first flight of the airplane.
BILLING CODE 4910-13-P
[[Page 30584]]
[GRAPHIC] [TIFF OMITTED] TR27JN19.000
[GRAPHIC] [TIFF OMITTED] TR27JN19.001
[[Page 30585]]
[GRAPHIC] [TIFF OMITTED] TR27JN19.002
[[Page 30586]]
[GRAPHIC] [TIFF OMITTED] TR27JN19.003
BILLING CODE 4910-13-C
(j) Retained Inspections of AD 2017-01-11, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2017-01-11, with no changes. For each MLG sliding tube identified as
required by paragraph (h) of this AD, having a part number and
serial number listed in table 1 to paragraphs (i), (j), (l)(1),
(l)(2), (m)(1), and (m)(2) of this AD: Within 3 months after
February 22, 2017 (the effective date of AD 2017-01-11) inspect
affected MLG axles and brake flanges by doing a detailed visual
inspection of the chromium plates for damage, and a Barkhausen noise
inspection of the MLG sliding tube axles for damage, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-32-1416, including Appendix 01, dated March 10, 2014. For Model
A318 series airplanes, use the procedures specified for Model A319
series airplanes in Airbus Service Bulletin A320-32-1416, including
Appendix 01, dated March 10, 2014.
(k) Retained Corrective Action of AD 2017-01-11, With No Changes
This paragraph restates the requirements of paragraph (j) of AD
2017-01-11, with no changes. If, during any inspection required by
paragraph (j) of this AD, any damage is detected: Before further
flight, replace the MLG sliding tube with a serviceable MLG sliding
tube, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-32-1416, including Appendix 01, dated March
10, 2014. For Model A318 series airplanes, use the procedures
specified for Model A319 series airplanes in Airbus Service Bulletin
A320-32-1416, including Appendix 01, dated March 10, 2014.
(l) Retained Definition of Serviceable MLG Sliding Tube of AD 2017-01-
11, With No Changes
This paragraph restates the definition specified in paragraph
(k) of AD 2017-01-11, with no changes. For the purpose of paragraph
(k) of this AD, a serviceable MLG sliding tube is defined as an MLG
sliding tube that meets the criterion in either paragraph (l)(1) or
(l)(2) of this AD.
(1) An MLG sliding tube having a part number and serial number
not listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2),
(m)(1), and (m)(2) of this AD.
(2) An MLG sliding tube having a part number and serial number
listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1),
and (m)(2) of this AD that has passed the inspections required by
paragraph (j) of this AD.
(m) Retained Parts Installation Prohibition of AD 2017-01-11, With No
Changes
This paragraph restates the requirements of paragraph (l) of AD
2017-01-11, with no changes.
(1) For airplanes that have an MLG sliding tube installed that
has a part number and serial number listed in table 1 to paragraphs
(i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD: After an
airplane is returned to service following accomplishment of the
actions required by paragraphs (h), (i), and (j) of this AD, no
person may install on any airplane an MLG sliding tube having a part
number and serial number listed in table 1 to paragraphs (i), (j),
(l)(1), (l)(2), (m)(1), and (m)(2) of this AD, unless that MLG
sliding tube has passed the inspection required by paragraph (j) of
this AD.
(2) For airplanes that, as of February 22, 2017 (the effective
date of AD 2017-01-11), do not have an MLG sliding tube installed
that has a part number and serial number listed in table 1 to
paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD:
No person may install, on any airplane, an MLG sliding tube having a
part number and serial number listed in table 1 to paragraphs (i),
(j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD unless that MLG
sliding tube has passed the inspection required by paragraph (j) of
this AD.
(n) New Definitions
For the purpose of paragraphs (o), (p), (q), (r), and (s) of
this AD the following definitions apply.
(1) Affected MLG shock absorber: An MLG shock absorber having a
part number and serial number as identified in Messier-Dowty Service
Bulletin 200-32-286, Revision 3, dated October 3, 2008, for Model
A318, A319, and A320 series airplanes; and Messier-Dowty Service
Bulletin 201-32-43, Revision 3, dated October 3, 2008, for Model
A321 series airplanes.
(2) Affected MLG sliding tube: An MLG sliding tube having a part
number and serial number as identified in Appendix B of Safran
Service Bulletin 200-32-321, Revision 2, dated October 3, 2017, for
Model A318, A319, and A320 series airplanes; or Safran Service
Bulletin 201-32-68, Revision 2, dated October 3, 2017, for Model
A321 series
[[Page 30587]]
airplanes, except those parts that passed an inspection as specified
in Safran Service Bulletin 200-32-321; or Safran Service Bulletin
201-32-68; as applicable; and those parts that, after that
inspection, have been repaired, using instructions approved by the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(3) Serviceable MLG sliding tube: An MLG sliding tube that is
not affected, or an affected MLG sliding tube, that has not exceeded
10,000 flight cycle since first installation on an airplane, or an
affected MLG sliding tube that, within the last 5,000 flight cycles
before installation on an airplane, passed an inspection specified
in Airbus Service Bulletin A320-32-1441.
(o) New Requirement of This AD: Repetitive Inspections
At the compliance time specified in figure 2 to paragraph (o) of
this AD, and thereafter at intervals not to exceed 5,000 flight
cycles: Do a detailed inspection of each affected MLG sliding tube,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
[GRAPHIC] [TIFF OMITTED] TR27JN19.004
Note 2 to paragraph (o): If no reliable data regarding the
number of flight cycles accumulated by the MLG sliding tube are
available, operators may refer to the guidance specified in Chapter
5.2, ``Traceability'', of Section 1, of Part 1 of the Airbus A318/
A319/A320/A321 Airworthiness Limitations Section.
(p) New Requirement of This AD: Corrective Actions
(1) If, during any inspection required by paragraph (o) of this
AD, any crack is detected on an MLG sliding tube: Before further
flight, replace that MLG sliding tube with a serviceable MLG sliding
tube, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
(2) Replacement of an MLG on an airplane with an MLG having a
serviceable MLG sliding tube installed is an acceptable method to
comply with the requirements of paragraph (p)(1) of this AD for that
airplane.
(q) New Requirement of This AD: Part Replacement
(1) Within 10 years after the effective date of this AD: Replace
each affected MLG sliding tube with an MLG sliding tube that is not
affected. Installation of an MLG sliding tube that is not affected
on an airplane constitutes terminating action for the repetitive
inspections required by paragraph (o) of this AD for that airplane.
(2) Replacement of an MLG on an airplane with an MLG that does
not have an affected MLG sliding tube installed is an acceptable
method to comply with the requirement of paragraph (q)(1) of this AD
for that airplane.
(r) New Requirement of This AD: Parts Installation Limitation
(1) As of the effective date of this AD no person may install on
any airplane an affected MLG shock absorber assembly containing a
discrepant MLG sliding tube part number.
(2) Do not install an affected MLG sliding tube on any airplane
as specified in paragraph (r)(2)(i) or (r)(2)(ii) of this AD, as
applicable.
(i) For an airplane with an affected MLG sliding tube installed
as of the effective date of this AD: After replacement of each
affected MLG sliding tube as required by paragraph (q) of this AD.
(ii) For an airplane that does not have an affected MLG sliding
tube installed as of the effective date of this AD: As of the
effective date of this AD.
(s) Identification of Airplanes Not Affected by Certain Requirements of
This AD
An airplane on which Airbus Modification 161202 or Modification
161346 has been installed in production is not affected by the
requirements of paragraphs (g), (h), (j), (o), and (q), of this AD,
provided it has been verified that no affected MLG sliding tube is
installed on that airplane.
(t) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before
June 29, 2007, using Airbus AOT A320-32A1273, Revision 01, dated May
6, 2004. This document was incorporated by reference in AD 2004-11-
13, Amendment 39-13659 (69 FR 31867, June 8, 2004).
(2) This paragraph provides credit for the initial inspection
and applicable corrective actions required by paragraphs (o) and (p)
of this AD if those actions were performed before the effective date
of this AD, using the Accomplishment Instructions in Airbus Service
Bulletin A320-32-1441, dated December 28, 2016.
(u) Service Information Exceptions
The service information specified in paragraph (g) of this AD
has instructions to send any cracked part to Messier-Dowty. This AD
does not include such a requirement, in accordance with the
procedures specified in paragraph (w)(2) of this AD.
(v) No Reporting Requirement
Although Airbus Service Bulletin A320-32-1441, Revision 01,
dated December 14, 2017, specifies to submit certain information to
the manufacturer, and specifies that action as ``RC,'' (required for
compliance) this AD does not include that requirement.
(w) Other FAA AD Provisions
(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 (x)(2) of this AD. Information
may be emailed to: [email protected].
(i) 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.
(ii) AMOCs approved previously for AD 2007-11-11 are approved as
AMOCs for the corresponding provisions of paragraph (g) of this AD.
(iii) AMOCs approved previously for AD 2017-01-11 are approved
as AMOCs for the corresponding provisions of paragraphs (h), (i),
(j), (k), (l), and (m) of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or 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
paragraphs (u) and (v) of this AD: If any service information
contains
[[Page 30588]]
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.
(x) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2018-0135, dated June 26, 2018, 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-2019-0017.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3223.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (y)(6), (y)(7), and (y)(8) of this AD.
(y) 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
August 1, 2019.
(i) Airbus Service Bulletin A320-32-1441, Revision 01, dated
December 14, 2017.
(ii) Messier-Dowty Service Bulletin 200-32-286, Revision 3,
dated October 3, 2008.
(iii) Messier-Dowty Service Bulletin 201-32-43, Revision 3,
dated October 3, 2008.
(iv) Safran Service Bulletin 200-32-321, Revision 2, dated
October 3, 2017.
(v) Safran Service Bulletin 201-32-68, Revision 2, dated October
3, 2017.
(4) The following service information was approved for IBR on
February 22, 2017 (82 FR 5362, January 18, 2017).
(i) Airbus Service Bulletin A320-32-1416, including Appendix 01,
dated March 10, 2014.
(ii) [Reserved]
(5) The following service information was approved for IBR on
June 29, 2007 (72 FR 29241, May 25, 2007).
(i) Airbus Service Bulletin A320-32A1273, Revision 02, including
Appendix 01, dated May 26, 2005.
(ii) [Reserved]
(6) For Airbus service information identified in this AD,
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93
36 96; fax +33 5 61 93 44 51; email [email protected];
internet https://www.airbus.com.
(7) For Safran and Messier-Dowty service information identified
in this AD, contact Safran Landing Systems, One Carbon Way, Walton,
KY 41094; telephone (859) 525-8583; fax (859) 485-8827; internet
https://www.safran-landing-systems.com.
(8) 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.
(9) 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, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on June 19, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-13545 Filed 6-26-19; 8:45 am]
BILLING CODE 4910-13-P
