Airworthiness Directives; Airbus SAS Airplanes, 47047-47053 [2018-19854]
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Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations
(3) For Models 35, 35A, 36, and 36A
airplanes: Within 24 months after October
23, 2018 (the effective date of this AD) or
within 400 landings after October 23, 2018
(the effective date of this AD), whichever
occurs first, replace the nose roller fitting,
nose roller support bracket, and adjacent rib
support structure with replacement parts by
following the Accomplishment Instructions
in Bombardier Learjet 35/36 SB 35/36–27–50
Recommended, dated September 11, 2017.
(4) For Models 55, 55B, and 55C airplanes:
Within 24 months after October 23, 2018 (the
effective date of this AD) or within 400
landings after October 23, 2018 (the effective
date of this AD), whichever occurs first,
replace the nose roller fitting, nose roller
support bracket, and adjacent rib support
structure with replacement parts by
following the Accomplishment Instructions
in Bombardier Learjet 55 SB 55–27–41
Recommended, dated September 11, 2017.
(5) For Model 60 airplanes: Within 12
months after October 23, 2018 (the effective
date of this AD) or within 200 landings after
October 23, 2018 (the effective date of this
AD), whichever occurs first, replace the nose
roller fitting, nose roller support bracket, and
adjacent rib support structure with
replacement parts by following the
Accomplishment Instructions in Bombardier
Learjet 60 SB 60–27–39 Recommended,
Revision 1, dated January 15, 2018.
(6) For all airplanes: Some compliance
times in this AD are presented in landings.
If you do not keep a record of the total
number of landings, then use a 1-to-1
conversion for hours time-in-service (TIS) to
landings. Example: 20 hours TIS = 20
landings.
(7) For Models 31, 31A, 35, 35A, 36, 36A,
55, 55B, 55C, and 60 airplanes: Although
Paragraph 3.B.(2) of the applicable SB for
these models that have modified flap roller
assemblies requires the operator to contact
Learjet Inc. for repair instructions, this AD
requires you do the repair using a method
approved by the Manager, Wichita ACO
Branch, FAA. For a repair method to be
approved by the Manager, Wichita ACO
Branch, as required by this paragraph, the
Manager’s approval letter must specifically
refer to this AD.
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(h) Credit for Previous Actions
For Model 60 airplanes: This AD allows
credit for actions required in paragraph (g)(5)
of this AD if done before the effective date
of this AD following Bombardier Learjet 60
SB 60–27–39 Recommended, Basic Issue,
dated September 11, 2017.
(i) No Reporting Requirement
Although Bombardier Learjet 28/29 SB 28/
29–27–31 Recommended, dated September
11, 2017; Bombardier Learjet 31 SB 31–27–
35 Recommended, dated September 11, 2017;
Bombardier Learjet 35/36 SB 35/36 –27–50
Recommended, dated September 11, 2017;
Bombardier Learjet 55 SB 55–27–41
Recommended, dated September 11, 2017;
and Bombardier Learjet 60 SB 60–27–39
Recommended, Revision 1, dated January 15,
2018, all specify to submit a compliance
response form to the manufacturer per
paragraph 3.E., this AD does not require that
action.
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(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Wichita 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 (k)(1) of
this AD.
(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.
47047
Issued in Kansas City, Missouri, on August
31, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division,
Aircraft Certification Service.
[FR Doc. 2018–19853 Filed 9–17–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0390; Product
Identifier 2017–NM–130–AD; Amendment
39–19397; AD 2018–18–18]
(k) Related Information
RIN 2120–AA64
For more information about this AD,
contact Tara Shawn, Aerospace Engineer,
Wichita ACO Branch, 1801 Airport Road,
Room 100, Wichita, Kansas 67209; telephone:
(316) 946–4141; fax: (316) 946–4107; email:
tara.shawn@faa.gov or Wichita-COS@faa.gov.
Airworthiness Directives; Airbus SAS
Airplanes
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Bombardier Learjet 28/29 Service
Bulletin (SB) 28/29–27–31 Recommended,
dated September 11, 2017;
(ii) Bombardier Learjet 31 SB 31–27–35
Recommended, dated September 11, 2017;
(iii) Bombardier Learjet 35/36 SB 35/36
–27–50 Recommended, dated September 11,
2017;
(iv) Bombardier Learjet 55 SB 55–27–41
Recommended, dated September 11, 2017;
and
(v) Bombardier Learjet 60 SB 60–27–39
Recommended, Revision 1, dated January 15,
2018.
(3) For service information identified in
this AD, contact Learjet, Inc., One Learjet
Way, Wichita, Kansas 67209; telephone: 316–
946–2000; email: ac.ict@
aero.bombardier.com; internet: https://
www.bombardier.com.
(4) You may view this service information
at the FAA, Policy and Innovation Division,
901 Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148. In
addition, you can access this service
information on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2017–1078.
(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.
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Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus SAS Model A300 series
airplanes. This AD was prompted by a
revision of an airworthiness limitation
items (ALI) document. This AD requires
revising the maintenance or inspection
program, as applicable, to incorporate
the specified maintenance requirements
and airworthiness limitations. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective October 23,
2018.
ADDRESSES:
SUMMARY:
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–
0390; 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 (phone: 800–647–5527) 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: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3225.
SUPPLEMENTARY INFORMATION:
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Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations
Discussion
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We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus SAS Model A300
series airplanes. The NPRM published
in the Federal Register on May 11, 2018
(83 FR 21955). The NPRM was
prompted by a revision of an ALI
document. The NPRM proposed to
require revising the maintenance or
inspection program, as applicable, to
incorporate the specified maintenance
requirements and airworthiness
limitations.
We are issuing this AD to address the
reduced structural integrity of the
airplane and possible loss of
controllability 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 2017–0145,
dated August 31, 2017 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus SAS Model A300 series
airplanes. The MCAI states:
Some airworthiness limitations previously
defined in A300 ALS [Airworthiness
Limitations Section] Part 1 have been
removed from that document and should
normally be included in an ALS Part 4.
Airbus does not plan to issue an ALS Part 4
for A300 aeroplanes.
Nevertheless, failure to comply with these
airworthiness limitations could result in an
unsafe condition.
For the reason described above, it has been
decided to require the application of these
airworthiness limitations through a separate
AD.
Previously, EASA issued AD 2013–0210
[which corresponds to FAA AD 2014–16–13,
Amendment 39–17937 (79 FR 51083, August
27, 2014) (‘‘AD 2014–16–13’’)] to require
implementation of airworthiness limitations
applicable to main landing gear (MLG) barrel
assembly, retraction actuator assembly,
linkage assembly and flanged duct, which
were previously defined in Revision 00 of
A300 ALS Part 1 but removed from Revision
01 of A300 ALS Part 1, adding those limits
as an Appendix to the AD.
Since EASA AD 2013–0210 was issued,
improvement of safe life component selection
resulted, among others, in removal of 15 nose
landing gear (NLG) parts from Revision 02 of
A300 ALS Part 1.
Consequently, this [EASA] AD retains the
requirements of EASA AD 2013–0210, which
is superseded, and requires, in addition to
the implementation of airworthiness
limitations already contained in EASA AD
2013–0210, the implementation of
airworthiness limitations applicable to NLG
barrel assembly and shock absorber
assembly, previously contained in Revision
01 of A300 ALS Part 1, as specified in
Appendix 1 of this AD.
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16:42 Sep 17, 2018
Jkt 244001
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–2018–
0390.
Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comment
received on the NPRM and the FAA’s
response to the comment.
Request To Supersede AD 2014–16–13
Airbus questioned the need to keep
AD 2014–16–13 and whether the
proposed AD should instead supersede
AD 2014–16–13. Airbus noted that the
proposed AD lists all of the ALIs in
EASA AD 2017–0145, dated August 31,
2017, not just the ALIs that have been
updated since we issued AD 2014–16–
13. We infer that Airbus wanted the
proposed AD changed to a supersedure
AD.
We disagree with the request to
change this AD to a supersedure AD. To
address the unsafe condition, we chose
to match EASA AD 2017–0145, dated
August 31, 2017, and include the same
ALIs. Because accomplishment of the
requirements of this AD terminates all
requirements of AD 2014–16–13, a
supersedure is not necessary. We have
not changed this AD in this regard.
Request To Release Related ADs at the
Same Time
Airbus requested that we release this
final rule at the same time as the
following related ADs to provide clarity
to operators. All four pending ADs are
related to the same removal of 15 nose
landing gear parts from ALS Part 1, on
different airplane models.
• Docket No. FAA–2018–0364,
Product Identifier 2017–NM–154–AD
(EASA AD 2017–0204, dated October
12, 2017).
• Docket No. FAA–2018–0365,
Product Identifier 2017–NM–155–AD
(EASA AD 2017–0203, dated October
12, 2017).
• Docket No. FAA–2018–0396,
Product Identifier 2017–NM–156–AD
(EASA AD 2017–0202, dated October
12, 2017).
We agree with the request insofar as
we can control the publication
schedule. While we cannot ensure that
all four will be published on the same
date, we will coordinate with the Office
of the Federal Register (OFR) and
attempt to issue all four final rules at the
same time.
Conclusion
We reviewed the relevant data,
considered the comments received, and
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determined that air safety and the
public interest require adopting this
final rule with the changes described
previously and minor editorial changes.
We have 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.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Costs of Compliance
We estimate that this AD affects 5
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
We have determined that revising the
maintenance or inspection program
takes an average of 90 work-hours per
operator, although we recognize that
this number may vary from operator to
operator. In the past, we have estimated
that this action takes 1 work-hour per
airplane. Since operators incorporate
maintenance or inspection program
changes for their affected fleet(s), we
have determined that a per-operator
estimate is more accurate than a perairplane estimate. Therefore, we
estimate the total cost per operator to be
$7,650 (90 work-hours × $85 per workhour).
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This 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
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Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations
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
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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) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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16:42 Sep 17, 2018
Jkt 244001
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):
■
2018–18–18 Airbus SAS: Amendment 39–
19397; Docket No. FAA–2018–0390;
Product Identifier 2017–NM–130–AD.
(a) Effective Date
This AD is effective October 23, 2018.
(b) Affected ADs
This AD affects AD 2014–16–13,
Amendment 39–17937 (79 FR 51083, August
27, 2014) (‘‘AD 2014–16–13’’).
(c) Applicability
This AD applies to Airbus SAS Model
A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–
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47049
2C, B4–103, and B4–203 airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 05, Time Limits/Maintenance
Checks.
(e) Reason
This AD was prompted by a revision of an
airworthiness limitation items (ALI)
document. We are issuing this AD to prevent
reduced structural integrity of the airplane
and possible loss of controllability of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Revision of Maintenance or Inspection
Program
Within 90 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to incorporate the
safe life limits included in figure 1 to
paragraph (g) of this AD. The initial
compliance time for the replacements is prior
to the applicable life limits specified in figure
1 to paragraph (g) of this AD, or within 90
days after the effective date of this AD,
whichever occurs later. The term ‘‘FH’’ in
figure 1 to paragraph (g) of this AD means
total flight hours. The term ‘‘LDG’’ in figure
1 to paragraph (g) of this AD means total
airplane landings.
BILLING CODE 4910–13–P
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47050
Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations
Figure 1 to paragraph (g) of this AD- New Life Limits for the Main Landing Gear
(MLG) Barrel Assembly, Retraction Actuator Assembly, Linkage Assembly; Pneumatic
Flange Duct; Nose Landing Gear (NLG) Barrel Assembly and Shock Absorber Assembly
SAFE LIFE LIMITS (*)
Part Number
FH
ATA 32-1~0 MAIN LANDING GEAR
BARREL ASSEMBLY
C66277-10
NJA
Stirrup
C66277-12
Cal
66600
N/A
X
X
X
X
76600
N/A
X
X
X
X
76600
N/A
X
X
X
X
76600
N/A
X
X
X
X
C66457
N/A
76600
N/A
X
X
X
X
048939
NJA
76600
N/A
X
X
X
X
048939-1
N/A
76600
N/A
X
X
X
X
058314-1
NJA
76600
N/A
X
X
X
X
C66279
NJA
76600
N/A
X
X
X
X
C66279-2
NJA
76600
N/A
X
X
X
X
C66279-6
NJA
76600
N/A
X
X
X
X
058313-1
NJA
76600
N/A
X
X
X
X
C61637-10
N/A
76600
N/A
X
X
C61637-11
X
NJA
76600
N/A
X
C61637-12
N/A
76600
N/A
X
X
C61638-10
N/A
53300
N/A
X
X
C61638-11
N/A
53300
N/A
X
X
C61638-20
NJA
76600
N/A
X
X
C68523-3
NJA
76600
N/A
X
X
X
C69028-4
N/A
34000
N/A
C69029-1 (1)
N/A
32000
N/A
X
X
X
X
C69029-2
N/A
32000
N/A
X
X
X
X
C69029-3
N/A
32000
N/A
X
N/A
22000
N/A
X
C67078
NJA
33000
N/A
X
X
X
X
X
X
C69029-4 (2)
X
X
C67078-1
N/A
33000
N/A
X
X
X
X
C61342-4
NJA
36700
N/A
C66510-4
NJA
32000
N/A
X
X
X
X
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Piston
End fitting
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B4-1xx
NJA
RETRACTION ACTUATOR ASSEMBLY
(1) When SB Al00-32-0123 embodied before SB Al00-32-0113.
I (2) When SB AJ00-32..0123 embodied after SB Al00-32..0113.
C69028-1
N/A
N/A 34000
X
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C4-203
F4-203
LOG
N/A
Tie rod
Sliding rod
Affected Model(s)
B4-2C 84_2xx
82-320
058303-1
Universal joint
Plate (Rear head
end)
82K-3C
B2-20x
C66277-14
Stirrup pin
Plate (Upper
end)
NJA
B2-1A
B2-1C
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Jkt 244001
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X
X
Sfmt 4725
X
X
X
X
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Part Name
47051
Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations
LINKAGE ASSEMBLY
C61505
NIA 76600
N/A
Upper
X
X
multiple link
C61505-1
N/A
X
NIA 76600
X
pin (Multiple
link/Upper
C61505-20
NIA 76600
NIA
X
X
linkS
ATA36-11-05 PNEUMATIC
(1) "xx" at the end of the PIN stands for anv number between 00 and 99.
Duct flanged ( 1) A2127~~63000
N/A
24000
N/A
X
X
X
End fitting pin
End fitting
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Rack
VerDate Sep<11>2014
AN6-17
N/A
(2)
N/A
X
X
X
X
N/A
N/A
N/A
(2)
(2)
(2)
N/A
N/A
N/A
X
X
X
X
X
061183
068063
NAS1306-22D
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
C62032
N/A
65700
N/A
X
X
X
X
X
X
C62032-1
N/A
65700
N/A
X
X
X
X
X
X
C62032-2
N/A
65700
N/A
X
X
X
X
X
X
C62032-10
061184
N/A
N/A
65700
65700
N/A
N/A
X
X
X
X
X
X
X
X
X
X
X
X
061184-1
N/A
65700
N/A
X
65700
N/A
X
X
N/A
N/A
65700
65700
N/A
NIA
X
X
X
068695
C61453
X
X
X
X
X
N/A
X
X
X
X
068076
X
X
X
X
X (1)
C61453-1
N/A
65700
N/A
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
C61453-15
N/A
65700
N/A
C61453-20
N/A
65700
N/A
C61453-40
N/A
65700
N/A
C61453-41
N/A
65700
N/A
X
X
X
X
C61453-205
N/A
65700
N/A
X
X
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ATA32-20-00 NOSE LANDING GEAR
BARREL ASSEMBLY (FIG.07)
(1) Limitation applicable to WV01 & WV03 only.
(2) Part must be replaced by a new one every time it is removed from the barrel.
(3) The nut must be replaced by a new one every time it is removed from the pin. When the nut is
temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no
replacement is required provided the nut's removal and reinstallation are performed on the same pin and
neither the pin nor the nut accumulates time in service during the period between the removal and
reinstallation.
N/A
(2)
N/A
X
X
X
X
X
068062
X
End fitting
pin nut
(2)
N/A
X
X
X
X
X
X
MS17825-6
N/A
47052
Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations
SAFE LIFE LIMITS (.,.)
Part Name
Turning tube
Part Number
FH
LOG
Cal
B2-1A
B2-1C
B2K-3C
B2-20x
82-320
C59050-30
N/A
24000
N/A
X
X
X
C59050-40
N/A
24000
N/A
X
X
X
C59050-50
N/A
65700
N/A
X
N/A
65700
N/A
X
X
X
X
C59050-60
C59050
N/A
24000
N/A
X
X(1)
C59050-2
N/A
24000
N/A
X
X(1)
C59050-3
Torque link pin
(Upper & Lower)
Torque Links
(Upper & Lower)
Torque link
medium pin
Affected Model(s)
24000
24000
N/A
N/A
X
C59050-4
NIA
N/A
X(1)
X
C59050-20
N/A
24000
N/A
X
X
X
C59050-28
N/A
24000
N/A
X
X(1)
C62223-1
N/A
65700
N/A
X
C62223-15
N/A
65700
N/A
C62223-20
N/A
65700
N/A
C59562-2
N/A
65700
N/A
X
X
X
X
X
X
X
C59562-3
N/A
65700
N/A
X
X
X
X
X
X
B4-2C
84-2xx
B4-1xx
C4-203
F4-203
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
C62041-1
N/A
65700
N/A
C62041-15
N/A
65700
N/A
C62041-20
N/A
65700
N/A
C62041-200
N/A
65700
N/A
X
X
X
X
X
X
053431
N/A
65700
N/A
X
X
X
X
X
X
X
X
X
053431-20
N/A
65700
N/A
X
X
X
X
X
A
X
X
X
X
C59562-4
N/A
65700
N/A
C59562-20
N/A
65700
N/A
~
SL40110P
lA
X
X
X
SHOCK ABSORBER ASSEMBLY
C62270
..
C62034-1
N/A
65700
N/A
C62034-10
NIA
65700
C68534
N/A
I
daltland on DSKBBV9HB2PROD with RULES
Upper cam
VerDate Sep<11>2014
16:42 Sep 17, 2018
Jkt 244001
~
PO 00000
X
X
X
X
X
X
X
X
X
X
X
NIA
X
X
X
X
X
X
65700
N/A
X
X
X
X
X
X
Frm 00026
Fmt 4700
,. TJ
Sfmt 4725
E:\FR\FM\18SER1.SGM
18SER1
ER18SE18.003</GPH>
(1) Limitation applicable to WV01 & WV03 only.
(2) Limitation applicable to WV 00 only.
(3) Limitation applicable to WV 08 only.
(4) Part must be replaced by a new one every time it is removed from the sliding rod.
(5) Part must be replaced by a new one every time it is removed from the upper rod.
Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations
(h) No Alternative Actions or Intervals
After the maintenance or inspection
program has been revised as required by
paragraph (g) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (j)(1) of
this AD.
daltland on DSKBBV9HB2PROD with RULES
(i) Terminating Action for AD 2014–16–13
Accomplishing the actions required by this
AD terminates all requirements of AD 2014–
16–13.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
VerDate Sep<11>2014
16:42 Sep 17, 2018
Jkt 244001
directly to the International Section, send it
to the attention of the person identified in
paragraph (k)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished 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.
https://www.regulations.gov by searching for
and locating Docket No. FAA–2018–0390.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3225.
(l) Material Incorporated by Reference
None.
Issued in Des Moines, Washington, on
August 24, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–19854 Filed 9–17–18; 8:45 am]
BILLING CODE 4910–13–P
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0145, dated August 31, 2017, for
related information. This MCAI may be
found in the AD docket on the internet at
PO 00000
Frm 00027
Fmt 4700
Sfmt 9990
E:\FR\FM\18SER1.SGM
18SER1
ER18SE18.004</GPH>
BILLING CODE 4910–13–P
47053
]]>Agencies
[Federal Register Volume 83, Number 181 (Tuesday, September 18, 2018)]
[Rules and Regulations]
[Pages 47047-47053]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-19854]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0390; Product Identifier 2017-NM-130-AD; Amendment
39-19397; AD 2018-18-18]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus SAS Model A300 series airplanes. This AD was prompted by a
revision of an airworthiness limitation items (ALI) document. This AD
requires revising the maintenance or inspection program, as applicable,
to incorporate the specified maintenance requirements and airworthiness
limitations. We are issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective October 23, 2018.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0390; 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 (phone: 800-647-
5527) 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: Dan Rodina, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.
SUPPLEMENTARY INFORMATION:
[[Page 47048]]
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus SAS Model A300
series airplanes. The NPRM published in the Federal Register on May 11,
2018 (83 FR 21955). The NPRM was prompted by a revision of an ALI
document. The NPRM proposed to require revising the maintenance or
inspection program, as applicable, to incorporate the specified
maintenance requirements and airworthiness limitations.
We are issuing this AD to address the reduced structural integrity
of the airplane and possible loss of controllability 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
2017-0145, dated August 31, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for all Airbus SAS Model A300 series
airplanes. The MCAI states:
Some airworthiness limitations previously defined in A300 ALS
[Airworthiness Limitations Section] Part 1 have been removed from
that document and should normally be included in an ALS Part 4.
Airbus does not plan to issue an ALS Part 4 for A300 aeroplanes.
Nevertheless, failure to comply with these airworthiness
limitations could result in an unsafe condition.
For the reason described above, it has been decided to require
the application of these airworthiness limitations through a
separate AD.
Previously, EASA issued AD 2013-0210 [which corresponds to FAA
AD 2014-16-13, Amendment 39-17937 (79 FR 51083, August 27, 2014)
(``AD 2014-16-13'')] to require implementation of airworthiness
limitations applicable to main landing gear (MLG) barrel assembly,
retraction actuator assembly, linkage assembly and flanged duct,
which were previously defined in Revision 00 of A300 ALS Part 1 but
removed from Revision 01 of A300 ALS Part 1, adding those limits as
an Appendix to the AD.
Since EASA AD 2013-0210 was issued, improvement of safe life
component selection resulted, among others, in removal of 15 nose
landing gear (NLG) parts from Revision 02 of A300 ALS Part 1.
Consequently, this [EASA] AD retains the requirements of EASA AD
2013-0210, which is superseded, and requires, in addition to the
implementation of airworthiness limitations already contained in
EASA AD 2013-0210, the implementation of airworthiness limitations
applicable to NLG barrel assembly and shock absorber assembly,
previously contained in Revision 01 of A300 ALS Part 1, as specified
in Appendix 1 of this AD.
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-2018-
0390.
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comment received on the
NPRM and the FAA's response to the comment.
Request To Supersede AD 2014-16-13
Airbus questioned the need to keep AD 2014-16-13 and whether the
proposed AD should instead supersede AD 2014-16-13. Airbus noted that
the proposed AD lists all of the ALIs in EASA AD 2017-0145, dated
August 31, 2017, not just the ALIs that have been updated since we
issued AD 2014-16-13. We infer that Airbus wanted the proposed AD
changed to a supersedure AD.
We disagree with the request to change this AD to a supersedure AD.
To address the unsafe condition, we chose to match EASA AD 2017-0145,
dated August 31, 2017, and include the same ALIs. Because
accomplishment of the requirements of this AD terminates all
requirements of AD 2014-16-13, a supersedure is not necessary. We have
not changed this AD in this regard.
Request To Release Related ADs at the Same Time
Airbus requested that we release this final rule at the same time
as the following related ADs to provide clarity to operators. All four
pending ADs are related to the same removal of 15 nose landing gear
parts from ALS Part 1, on different airplane models.
Docket No. FAA-2018-0364, Product Identifier 2017-NM-154-
AD (EASA AD 2017-0204, dated October 12, 2017).
Docket No. FAA-2018-0365, Product Identifier 2017-NM-155-
AD (EASA AD 2017-0203, dated October 12, 2017).
Docket No. FAA-2018-0396, Product Identifier 2017-NM-156-
AD (EASA AD 2017-0202, dated October 12, 2017).
We agree with the request insofar as we can control the publication
schedule. While we cannot ensure that all four will be published on the
same date, we will coordinate with the Office of the Federal Register
(OFR) and attempt to issue all four final rules at the same time.
Conclusion
We 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. We have 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.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Costs of Compliance
We estimate that this AD affects 5 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
We have determined that revising the maintenance or inspection
program takes an average of 90 work-hours per operator, although we
recognize that this number may vary from operator to operator. In the
past, we have estimated that this action takes 1 work-hour per
airplane. Since operators incorporate maintenance or inspection program
changes for their affected fleet(s), we have determined that a per-
operator estimate is more accurate than a per-airplane estimate.
Therefore, we estimate the total cost per operator to be $7,650 (90
work-hours x $85 per work-hour).
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This 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
[[Page 47049]]
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
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) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
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 adding the following new airworthiness
directive (AD):
2018-18-18 Airbus SAS: Amendment 39-19397; Docket No. FAA-2018-0390;
Product Identifier 2017-NM-130-AD.
(a) Effective Date
This AD is effective October 23, 2018.
(b) Affected ADs
This AD affects AD 2014-16-13, Amendment 39-17937 (79 FR 51083,
August 27, 2014) (``AD 2014-16-13'').
(c) Applicability
This AD applies to Airbus SAS Model A300 B2-1A, B2-1C, B2K-3C,
B2-203, B4-2C, B4-103, and B4-203 airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 05, Time Limits/
Maintenance Checks.
(e) Reason
This AD was prompted by a revision of an airworthiness
limitation items (ALI) document. We are issuing this AD to prevent
reduced structural integrity of the airplane and possible loss of
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Revision of Maintenance or Inspection Program
Within 90 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to incorporate the
safe life limits included in figure 1 to paragraph (g) of this AD.
The initial compliance time for the replacements is prior to the
applicable life limits specified in figure 1 to paragraph (g) of
this AD, or within 90 days after the effective date of this AD,
whichever occurs later. The term ``FH'' in figure 1 to paragraph (g)
of this AD means total flight hours. The term ``LDG'' in figure 1 to
paragraph (g) of this AD means total airplane landings.
BILLING CODE 4910-13-P
[[Page 47050]]
[GRAPHIC] [TIFF OMITTED] TR18SE18.001
[[Page 47051]]
[GRAPHIC] [TIFF OMITTED] TR18SE18.002
[[Page 47052]]
[GRAPHIC] [TIFF OMITTED] TR18SE18.003
[[Page 47053]]
[GRAPHIC] [TIFF OMITTED] TR18SE18.004
BILLING CODE 4910-13-P
(h) No Alternative Actions or Intervals
After the maintenance or inspection program has been revised as
required by paragraph (g) of this AD, no alternative actions (e.g.,
inspections) or intervals may be used unless the actions or
intervals are approved as an alternative method of compliance (AMOC)
in accordance with the procedures specified in paragraph (j)(1) of
this AD.
(i) Terminating Action for AD 2014-16-13
Accomplishing the actions required by this AD terminates all
requirements of AD 2014-16-13.
(j) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (k)(2) of this AD. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: 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 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.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0145, dated August 31, 2017, 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-2018-0390.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3225.
(l) Material Incorporated by Reference
None.
Issued in Des Moines, Washington, on August 24, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-19854 Filed 9-17-18; 8:45 am]
BILLING CODE 4910-13-P
