Airworthiness Directives; Airbus Airplanes, 39351-39355 [2017-16359]
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Federal Register / Vol. 82, No. 159 / Friday, August 18, 2017 / Rules and Regulations
(n) Exceptions to Service Information
Specifications
Subtask 271257–832–006–001 of Airbus
Service Bulletin A320–27–1257, Revision 01,
dated January 1, 2017, includes incorrect
instructions. This AD requires that those
instructions be followed as specified in
paragraphs (n)(1) and (n)(2) of this AD.
(1) For Subtask 271257–832–006–001,
instruction ‘‘(b)’’: If SEC C 126 software P/N
B372CAM0104 is found, no further action is
required by this AD.
(2) For Subtask 271257–832–006–001,
instruction ‘‘(c)’’: If SEC C 122 software P/N
B372CAM0101, SEC C 124 software P/N
B372CAM0102, or SEC C 125 software P/N
B372CAM0103 is found, do corrective
actions using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA.
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.
(q) Special Flight Permits
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
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(o) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (i) of this AD,
if those actions were performed before the
effective date of this AD using the applicable
service information specified in paragraph
(o)(1) or (o)(2) of this AD.
(1) For airplanes that have received Airbus
modification 39429 (installation of SEC
hardware C P/N B372CAM0100) in
production: Airbus Service Bulletin A320–
27–1252, dated November 6, 2015.
(2) For airplanes that have not received
Airbus modification 39429 in production:
Airbus Service Bulletin A320–27–1257,
dated December 18, 2015.
(p) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 Branch, send it to the
attention of the person identified in
paragraph (r)(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. The AMOC approval letter
must specifically reference this AD.
(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 Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (n) of this AD: If
any service information contains procedures
or tests that are identified as RC, those
(s) 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 September 22, 2017.
(i) Airbus Service Bulletin A320–27–1252,
Revision 01, dated February 18, 2016.
(ii) Airbus Service Bulletin A320–27–1257,
Revision 01, dated January 1, 2017.
(4) The following service information was
approved for IBR on November 20, 2015 (80
FR 68429, November 5, 2015).
(i) Airbus A318/A319/A320/A321
Temporary Revision TR572, Issue 1.0, dated
August 13, 2015, to the Airbus A318/A319/
A320/A321 Airplane Flight Manual.
(ii) Reserved.
(5) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 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.
You may view this referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(6) You may view this service information
at the FAA, Transport Airplane Directorate,
15:59 Aug 17, 2017
Jkt 241001
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on June 29,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–14471 Filed 8–17–17; 8:45 am]
BILLING CODE 4910–13–P
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0056, dated
March 18, 2016, 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–
2016–9508.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (s)(5) and (s)(6) of this AD.
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39351
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9052; Product
Identifier 2016–NM–080–AD; Amendment
39–18983; AD 2017–16–06]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A300 series airplanes;
Model A300 B4–600, B4–600R, and F4–
600R series airplanes, and Model A300
C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes); and Model A310 series
airplanes. This AD was prompted by
reports of failure of an aft hinge bolt
assembly in the nose landing gear (NLG)
aft doors. This AD requires replacement
of the aft hinge bolt assembly in the left
and right NLG aft doors, with new aft
hinge bolt assemblies. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective September
22, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 22, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAW, 1 Rond Point Maurice Bellonte,
31707 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://
SUMMARY:
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www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
It is also available on the Internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2016–
9052.
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–2016–
9052; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
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, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–
1149.
SUPPLEMENTARY INFORMATION:
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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 Model A300 series
airplanes; Model A300 B4–600, B4–
600R, and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes); and Model
A310 series airplanes. The NPRM
published in the Federal Register on
August 30, 2016 (81 FR 59546) (‘‘the
NPRM’’). The NPRM was prompted by
reports of failure of an aft hinge bolt
assembly in the NLG aft doors. The
NPRM proposed to require replacement
of the aft hinge bolt assembly in the left
and right NLG aft doors, with new aft
hinge bolt assemblies. We are issuing
this AD to prevent failure of an aft hinge
bolt assembly in an NLG aft door while
the airplane is in flight, which could
lead to an in-flight loss of an NLG aft
door, and damage to 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 2016–0100,
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15:59 Aug 17, 2017
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dated May 24, 2016 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A300 series
airplanes; Model A300 B4–600, B4–
600R, and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes); and Model
A310 series airplanes. The MCAI states:
An occurrence has been reported of failure
of a nose landing gear (NLG) door aft hinge
bolt assembly, Part Number (P/N)
A53612600000. The result of laboratory
investigations revealed that the aft hinge bolt
rupture was initiated by fatigue crack
development in the under head radius of the
bolt, due to the lack of radius roll over and
in combination with a non-optimised design.
This condition, if not detected and
corrected, could lead to in-flight loss of an aft
NLG door, possibly resulting in damage to
the aeroplane and injury to persons on the
ground.
Prompted by these findings, Airbus
developed a new design aft hinge bolt
assembly P/N A53612713000, introduced as
Airbus modification (mod) 13741, to replace
the existing bolt P/N A53612600000. Since
the introduction of that mod, additional
stress calculations demonstrated that the new
bolt assembly, P/N A53612713000, cannot
sustain fatigue loads up to the design Limit
of Validity (LOV) of the affected aeroplanes.
To address this potential unsafe condition,
Airbus issued Service Bulletin (SB) A300–
53–0397, SB A310–53–2144 and SB A300–
53–6186, to provide instructions for the
repetitive replacement of the affected postmod 13741 P/N A53612713000 aft hinge
bolts.
For the reasons described above, this
[EASA] AD requires the replacement of all
P/N A53612600000 aft hinge bolt assemblies,
installed on the left hand (LH) and right hand
(RH) NLG aft doors, with post-mod 13741 P/
N A53612713000 aft hinge bolt assemblies,
and, subsequently, the implementation of a
life limit for those new bolt assemblies.
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–2016–
9052.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Withdraw the NPRM
FedEx stated it does not agree that the
proposed hinge bolt replacement is
necessary, asserting that the severity of
a failed condition does not equate to an
unsafe condition on the airplane. FedEx
explained that in the last 22 years of
flight operations, it has not had a
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departure of the NLG door, nor has it
seen any cracking of the aft hinge bolt.
From this statement, we infer that
FedEx requested we withdraw the
NPRM. We disagree with this request.
Airbus has records of multiple instances
of hinge bolt failures. Failure of an aft
hinge bolt assembly in an NLG aft door
while the airplane is in flight could lead
to an in-flight loss of an NLG aft door,
and damage to the airplane. We have
not changed this AD in this regard.
Request To Allow Option for Repetitive
Inspections
FedEx requested that a repetitive nondestructive test (NDT) technique be
allowed as an option to replacing the
affected bolts. FedEx stated that a
routine NDT inspection would be best
suited for this condition and that the
affected bolts should only be replaced as
an on-condition action. Further, FedEx
stated that the proposed requirement to
replace all affected bolts will be a
financial burden on operators. FedEx
also pointed out that the two bolts
required for each airplane are $2,300,
and these bolts will be required to be
replaced every 10,000 flight cycles
(approximately every 10 years). FedEx
further requested that the FAA petition
the EASA to revise the Airbus service
information to permit the repetitive
inspection as an option to the required
bolt replacement.
We disagree with the commenter’s
request. The intent of this AD is to
regularly replace the affected hinge bolt
with a new one. The bolt loading and
fatigue spectrum is complex, and the
manufacturer is not able to substantiate
a fatigue life to support a repeat
inspection program. Therefore, we have
made no changes to this AD in this
regard. However, under the provisions
of paragraph (k)(1) of this AD, we will
consider requests for approval of an
alternative method of compliance
(AMOC) if sufficient data are submitted
to substantiate that the change would
provide an acceptable level of safety.
Request To Remove the Requirement To
Replace Aft Hinge Bolts
United Parcel Service (UPS) requested
that we revise the proposed AD to
remove the requirement to replace aft
hinge bolts. UPS contended that the
more appropriate method for
implementation of the repetitive 10,000flight-cycle replacement of the hinge
bolt assembly would be through a
maintenance program revision, or
incorporation into the Safe Life
Airworthiness Limitation Items (SL
ALI)—Part 1. Therefore, UPS
recommended that we delete the
proposed hinge bolt replacement, and
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instead coordinate with EASA to revise
the SL ALI to include the hinge bolt
assembly.
We disagree with the commenter’s
request. Only parts that are identified as
a safe life part are incorporated into the
SL ALI. The specified hinge bolt does
not meet the Airbus Airworthiness
Limitations Section (ALS) Part 1 criteria
for a safe life part. The hinge bolt does
not have fatigue testing or demonstrated
fatigue life analysis, which is required
for safe life parts. We have not changed
this AD in this regard.
Request To Combine Certain Service
Information
UPS requested that, if its request to
revise the proposed AD to remove the
hinge assembly replacement is
unacceptable to the FAA, we revise
paragraph (h)(3) of this proposed AD to
require removal and installation of a
new bolt using only Airbus Service
Bulletin A300–53–6182 and not list
Airbus Service Bulletin A300–53–6186.
UPS explained that the final result of
the proposed AD is the replacement of
the bolt in every case; however, Airbus
Service Bulletin A300–53–6186
specifies doing an inspection of the bolt
part number in addition to the
replacement and is an added burden to
the operator given the location of the
identifying mark and the difficulty
accessing that mark.
We disagree with the commenter’s
request because paragraphs (g) and (h)
of this AD and the corresponding
service information are necessary to
distinguish between two different
actions with different compliance times:
• Paragraph (g) of this AD and
corresponding service information for
the introduction of the bolt’s new
design.
• Paragraph (h) of this AD and
corresponding service bulletin for
regular bolt replacement, which
includes an inspection for verification if
the proper bolt part number was
installed.
While it might be difficult for
operators to identify the part number of
the bolt when it is installed on the
aircraft, the bolt is scheduled to be
removed so it should not be difficult to
verify that the correct part was installed.
We have not changed this AD in this
regard.
Request To Update Illustrated Parts
Catalog (IPC) To Show the PostModification Part Number
UPS requested that the FAA
coordinate with EASA and Airbus to
ensure that the IPC is updated to show
only the post-modification part number
prior to the AD being issued. UPS was
concerned that an outdated IPC creates
opportunities for installation of the
original, non-compliant bolt assembly.
We infer that UPS was also requesting
that we delay publication of the final
rule pending revision of the IPC. We
disagree with this request. Airbus has
informed the FAA that the IPC is
scheduled to be revised. However, we
do not consider that delaying this action
until after the release of the
manufacturer’s revised IPC is warranted,
since sufficient information currently
exists in this AD and the required
service information to address the
identified unsafe condition. We have
not changed this AD in this regard.
Clarification of Corrective Action
We have clarified the corrective
actions in the introductory text of
paragraph (h) of this AD by referring to
paragraph (k)(2) of this AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
39353
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
We reviewed the following Airbus
service information.
• Airbus Service Bulletin A300–53–
0396, dated November 25, 2015.
• Airbus Service Bulletin A300–53–
6182, dated November 17, 2015.
• Airbus Service Bulletin A310–53–
2142, dated November 17, 2015.
This service information describes
procedures for replacement of the aft
hinge bolt assemblies in the left and
right NLG aft doors, with new aft hinge
bolt assemblies. These documents are
distinct since they apply to different
airplane models and configurations.
We also reviewed the following
Airbus service information.
• Airbus Service Bulletin A300–53–
0397, dated January 18, 2016.
• Airbus Service Bulletin A300–53–
6186, dated January 18, 2016.
• Airbus Service Bulletin A310–53–
2144, dated January 18, 2016.
This service information describes
procedures for replacement of the aft
hinge bolt assemblies in the left and
right NLG aft doors, with new aft hinge
bolt assemblies. The replacement
includes an inspection to verify if the
proper bolt part number was installed
and repair if the proper bolt part
number was not installed. These
documents are distinct since they apply
to different airplane models and
configurations.
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
We estimate that this AD affects 157
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Labor cost
Replacement ...........................
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Action
9 work-hours × $85 per hour = $765 .....................................
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
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15:59 Aug 17, 2017
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Parts cost
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
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$2,000
Cost per
product
$2,765
Cost on U.S.
operators
$434,105
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
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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 to the Director of the System
Oversight Division.
Regulatory Findings
We 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. 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
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):
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■
2017–16–06 Airbus: Amendment 39–18983;
Docket No. FAA–2016–9052; Product
Identifier 2016–NM–080–AD.
(a) Effective Date
This AD is effective September 22, 2017.
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15:59 Aug 17, 2017
Jkt 241001
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus airplanes
identified in paragraphs (c)(1) through (c)(6)
of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Model A300 B2–1A, B2–1C, B2K–3C,
B2–203, B4–2C, B4–103, and B4–203
airplanes.
(2) Model A300 B4–601, B4–603, B4–620,
and B4–622 airplanes.
(3) Model A300 B4–605R and B4–622R
airplanes.
(4) Model A300 F4–605R and F4–622R
airplanes.
(5) Model A300 C4–605R Variant F
airplanes.
(6) Model A310–203, –204, –221, –222,
–304, –322, –324, and –325 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of failure
of an aft hinge bolt assembly in the nose
landing gear (NLG) aft doors. We are issuing
this AD to prevent failure of an aft hinge bolt
assembly in an NLG aft door while the
airplane is in flight, which could lead to an
in-flight loss of an NLG aft door, and damage
to the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Replacement of Aft Hinge Bolt
Assemblies Having Part Number (P/N)
A53612600000
Before the accumulation of 10,000 total
flight cycles since first flight of the airplane,
or within 2,000 flight cycles after the
effective date of this AD, whichever occurs
later: Replace each aft hinge bolt assembly
having P/N A53612600000 on the left and
right NLG aft doors, with a new hinge bolt
assembly having P/N A53612713000, in
accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraph (g)(1),
(g)(2), or (g)(3) of this AD.
(1) Airbus Service Bulletin A300–53–0396,
dated November 25, 2015.
(2) Airbus Service Bulletin A310–53–2142,
dated November 17, 2015.
(3) Airbus Service Bulletin A300–53–6182,
dated November 17, 2015.
(h) Replacement of Aft Hinge Bolt
Assemblies Having P/N A53612713000
Within 10,000 flight cycles after
modification of an airplane as required by
paragraph (g) of this AD: Replace each aft
hinge bolt assembly having P/N
A53612713000 on the left and right NLG aft
doors, with a new aft hinge bolt assembly
having P/N A53612713000 on the left and
right NLG aft doors, in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraph (h)(1), (h)(2), or (h)(3) of this AD,
except where the service information
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specified in paragraph (h)(1), (h)(2), or (h)(3)
of this AD specifies to contact Airbus for
instructions, before further flight repair using
the procedure in paragraph (k)(2) of this AD.
Repeat the replacement thereafter at intervals
not to exceed 10,000 flight cycles.
(1) Airbus Service Bulletin A300–53–0397,
dated January 18, 2016.
(2) Airbus Service Bulletin A310–53–2144,
dated January 18, 2016.
(3) Airbus Service Bulletin A300–53–6186,
dated January 18, 2016.
(i) Parts Installation Prohibition (P/N
A53612600000)
After modification of an airplane NLG aft
door as required by paragraph (g) of this AD,
do not install an aft hinge bolt assembly
having P/N A53612600000 on any NLG aft
door of that airplane.
(j) Parts Installation Limitation (P/N
A53612713000)
After removal of an aft hinge bolt assembly
having P/N A53612713000 from an airplane
NLG aft door, as required by paragraph (h) of
this AD, do not install an aft hinge bolt
assembly having that part number on that
airplane unless it is a new aft hinge bolt
assembly.
(k) 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 (l)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOC–
REQUESTS@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’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
E:\FR\FM\18AUR1.SGM
18AUR1
Federal Register / Vol. 82, No. 159 / Friday, August 18, 2017 / Rules and Regulations
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0100, dated
May 24, 2016, 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–
2016–9052.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone 425–
227–2125; fax 425–227–1149.
(m) Material Incorporated by Reference
mstockstill on DSK30JT082PROD with RULES
(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.
(i) Airbus Service Bulletin A300–53–0396,
dated November 25, 2015.
(ii) Airbus Service Bulletin A300–53–0397,
dated January 18, 2016.
(iii) Airbus Service Bulletin A300–53–
6182, dated November 17, 2015.
(iv) Airbus Service Bulletin A300–53–
6186, dated January 18, 2016.
(v) Airbus Service Bulletin A310–53–2142,
dated November 17, 2015.
(vi) Airbus Service Bulletin A310–53–
2144, dated January 18, 2016.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 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.
(4) You may view this service information
at the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(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 Renton, Washington, on July 26,
2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–16359 Filed 8–17–17; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
15:59 Aug 17, 2017
Jkt 241001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0068; Product
Identifier 2014–SW–076–AD; Amendment
39–18981; AD 2017–16–04]
RIN 2120–AA64
Airworthiness Directives; Romtex
Anjou Aeronautique (Romtex) Torso
Restraint Systems
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Romtex
torso restraint systems (restraint
systems) installed on but not limited to
Airbus Helicopters Model AS350B2,
AS350B3, EC130B4, EC130T2, and
AS355NP helicopters. This AD requires
replacing certain restraint system
buckles. This AD was prompted by a
report of several restraint system buckle
knobs breaking. The actions of this AD
are intended to correct an unsafe
condition on these products.
DATES: This AD is effective September
22, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of September 22, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Romtex Anjou Aeronautique, Strada
Livezii nr. 98, 550042, Sibiu, Romania;
telephone +40 269 243 918; email
seatbelts@anjouaero.com. You may
review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0068.
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–2017–
0068; or in person at the Docket
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the European Aviation
Safety Agency (EASA) AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Frm 00021
Fmt 4700
Sfmt 4700
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
David Hatfield, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5116; email
david.hatfield@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
SUMMARY:
PO 00000
39355
On February 17, 2017, at 82 FR 10971,
the Federal Register published our
notice of proposed rulemaking (NPRM),
which proposed to amend 14 CFR part
39 by adding an AD that would apply
to Romtex restraint systems with a
rotary buckle sub-assembly (buckle
assembly) with a part number and serial
number listed in Romtex Service
Bulletin No. 358SB–14–101, Revision 1,
dated December 12, 2014. These
restraint systems are installed on, but
not limited to, Airbus Helicopters
Model AS350B2, AS350B3, EC130B4,
EC130T2, and AS355NP helicopters.
The NPRM proposed to require
inspecting the buckle assembly to
determine whether the straps release,
marking the seat as inoperative if the
buckle fails to release the straps, and
replacing the buckle assembly within
180 hours time-in-service (TIS). The
NPRM also proposed to prohibit
installing the affected buckle assemblies
on any helicopter. The proposed
requirements were intended to prevent
a restraint system strap from failing to
release from the buckle, preventing
occupants from exiting the helicopter
during an emergency.
The NPRM was prompted by AD No.
2014–0279, dated December 19, 2014,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for Romtex Model 358 torso
restraint systems installed on Airbus
Helicopters Model EC130T2, AS350B2,
and AS350B3 helicopters. EASA advises
that ruptures have occurred on the
upper side (knob) of several rotary
buckles installed on these restraint
systems. EASA states the material used
in two batches of the buckle assembly
were altered by a supplier, resulting in
a specification different from the
approved design data. The EASA AD
states that this condition could prevent
the release of the restraint system straps
as intended after an emergency landing.
To address this unsafe condition, the
EASA AD requires inspecting the buckle
E:\FR\FM\18AUR1.SGM
18AUR1
Agencies
[Federal Register Volume 82, Number 159 (Friday, August 18, 2017)]
[Rules and Regulations]
[Pages 39351-39355]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16359]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9052; Product Identifier 2016-NM-080-AD; Amendment
39-18983; AD 2017-16-06]
RIN 2120-AA64
Airworthiness Directives; Airbus 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 Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and Model A300 C4-605R Variant F airplanes
(collectively called Model A300-600 series airplanes); and Model A310
series airplanes. This AD was prompted by reports of failure of an aft
hinge bolt assembly in the nose landing gear (NLG) aft doors. This AD
requires replacement of the aft hinge bolt assembly in the left and
right NLG aft doors, with new aft hinge bolt assemblies. We are issuing
this AD to address the unsafe condition on these products.
DATES: This AD is effective September 22, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 22,
2017.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 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://
[[Page 39352]]
www.airbus.com. You may view this referenced service information at the
FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call 425-
227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9052.
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-2016-
9052; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, 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, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-
1149.
SUPPLEMENTARY INFORMATION:
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 Model A300
series airplanes; Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes); and Model A310 series
airplanes. The NPRM published in the Federal Register on August 30,
2016 (81 FR 59546) (``the NPRM''). The NPRM was prompted by reports of
failure of an aft hinge bolt assembly in the NLG aft doors. The NPRM
proposed to require replacement of the aft hinge bolt assembly in the
left and right NLG aft doors, with new aft hinge bolt assemblies. We
are issuing this AD to prevent failure of an aft hinge bolt assembly in
an NLG aft door while the airplane is in flight, which could lead to an
in-flight loss of an NLG aft door, and damage to 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
2016-0100, dated May 24, 2016 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus Model A300 series airplanes; Model A300
B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R
Variant F airplanes (collectively called Model A300-600 series
airplanes); and Model A310 series airplanes. The MCAI states:
An occurrence has been reported of failure of a nose landing
gear (NLG) door aft hinge bolt assembly, Part Number (P/N)
A53612600000. The result of laboratory investigations revealed that
the aft hinge bolt rupture was initiated by fatigue crack
development in the under head radius of the bolt, due to the lack of
radius roll over and in combination with a non-optimised design.
This condition, if not detected and corrected, could lead to in-
flight loss of an aft NLG door, possibly resulting in damage to the
aeroplane and injury to persons on the ground.
Prompted by these findings, Airbus developed a new design aft
hinge bolt assembly P/N A53612713000, introduced as Airbus
modification (mod) 13741, to replace the existing bolt P/N
A53612600000. Since the introduction of that mod, additional stress
calculations demonstrated that the new bolt assembly, P/N
A53612713000, cannot sustain fatigue loads up to the design Limit of
Validity (LOV) of the affected aeroplanes.
To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A300-53-0397, SB A310-53-2144 and SB A300-53-
6186, to provide instructions for the repetitive replacement of the
affected post-mod 13741 P/N A53612713000 aft hinge bolts.
For the reasons described above, this [EASA] AD requires the
replacement of all P/N A53612600000 aft hinge bolt assemblies,
installed on the left hand (LH) and right hand (RH) NLG aft doors,
with post-mod 13741 P/N A53612713000 aft hinge bolt assemblies, and,
subsequently, the implementation of a life limit for those new bolt
assemblies.
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-2016-
9052.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Withdraw the NPRM
FedEx stated it does not agree that the proposed hinge bolt
replacement is necessary, asserting that the severity of a failed
condition does not equate to an unsafe condition on the airplane. FedEx
explained that in the last 22 years of flight operations, it has not
had a departure of the NLG door, nor has it seen any cracking of the
aft hinge bolt.
From this statement, we infer that FedEx requested we withdraw the
NPRM. We disagree with this request. Airbus has records of multiple
instances of hinge bolt failures. Failure of an aft hinge bolt assembly
in an NLG aft door while the airplane is in flight could lead to an in-
flight loss of an NLG aft door, and damage to the airplane. We have not
changed this AD in this regard.
Request To Allow Option for Repetitive Inspections
FedEx requested that a repetitive non-destructive test (NDT)
technique be allowed as an option to replacing the affected bolts.
FedEx stated that a routine NDT inspection would be best suited for
this condition and that the affected bolts should only be replaced as
an on-condition action. Further, FedEx stated that the proposed
requirement to replace all affected bolts will be a financial burden on
operators. FedEx also pointed out that the two bolts required for each
airplane are $2,300, and these bolts will be required to be replaced
every 10,000 flight cycles (approximately every 10 years). FedEx
further requested that the FAA petition the EASA to revise the Airbus
service information to permit the repetitive inspection as an option to
the required bolt replacement.
We disagree with the commenter's request. The intent of this AD is
to regularly replace the affected hinge bolt with a new one. The bolt
loading and fatigue spectrum is complex, and the manufacturer is not
able to substantiate a fatigue life to support a repeat inspection
program. Therefore, we have made no changes to this AD in this regard.
However, under the provisions of paragraph (k)(1) of this AD, we will
consider requests for approval of an alternative method of compliance
(AMOC) if sufficient data are submitted to substantiate that the change
would provide an acceptable level of safety.
Request To Remove the Requirement To Replace Aft Hinge Bolts
United Parcel Service (UPS) requested that we revise the proposed
AD to remove the requirement to replace aft hinge bolts. UPS contended
that the more appropriate method for implementation of the repetitive
10,000-flight-cycle replacement of the hinge bolt assembly would be
through a maintenance program revision, or incorporation into the Safe
Life Airworthiness Limitation Items (SL ALI)--Part 1. Therefore, UPS
recommended that we delete the proposed hinge bolt replacement, and
[[Page 39353]]
instead coordinate with EASA to revise the SL ALI to include the hinge
bolt assembly.
We disagree with the commenter's request. Only parts that are
identified as a safe life part are incorporated into the SL ALI. The
specified hinge bolt does not meet the Airbus Airworthiness Limitations
Section (ALS) Part 1 criteria for a safe life part. The hinge bolt does
not have fatigue testing or demonstrated fatigue life analysis, which
is required for safe life parts. We have not changed this AD in this
regard.
Request To Combine Certain Service Information
UPS requested that, if its request to revise the proposed AD to
remove the hinge assembly replacement is unacceptable to the FAA, we
revise paragraph (h)(3) of this proposed AD to require removal and
installation of a new bolt using only Airbus Service Bulletin A300-53-
6182 and not list Airbus Service Bulletin A300-53-6186. UPS explained
that the final result of the proposed AD is the replacement of the bolt
in every case; however, Airbus Service Bulletin A300-53-6186 specifies
doing an inspection of the bolt part number in addition to the
replacement and is an added burden to the operator given the location
of the identifying mark and the difficulty accessing that mark.
We disagree with the commenter's request because paragraphs (g) and
(h) of this AD and the corresponding service information are necessary
to distinguish between two different actions with different compliance
times:
Paragraph (g) of this AD and corresponding service
information for the introduction of the bolt's new design.
Paragraph (h) of this AD and corresponding service
bulletin for regular bolt replacement, which includes an inspection for
verification if the proper bolt part number was installed.
While it might be difficult for operators to identify the part
number of the bolt when it is installed on the aircraft, the bolt is
scheduled to be removed so it should not be difficult to verify that
the correct part was installed. We have not changed this AD in this
regard.
Request To Update Illustrated Parts Catalog (IPC) To Show the Post-
Modification Part Number
UPS requested that the FAA coordinate with EASA and Airbus to
ensure that the IPC is updated to show only the post-modification part
number prior to the AD being issued. UPS was concerned that an outdated
IPC creates opportunities for installation of the original, non-
compliant bolt assembly.
We infer that UPS was also requesting that we delay publication of
the final rule pending revision of the IPC. We disagree with this
request. Airbus has informed the FAA that the IPC is scheduled to be
revised. However, we do not consider that delaying this action until
after the release of the manufacturer's revised IPC is warranted, since
sufficient information currently exists in this AD and the required
service information to address the identified unsafe condition. We have
not changed this AD in this regard.
Clarification of Corrective Action
We have clarified the corrective actions in the introductory text
of paragraph (h) of this AD by referring to paragraph (k)(2) of this
AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
We reviewed the following Airbus service information.
Airbus Service Bulletin A300-53-0396, dated November 25,
2015.
Airbus Service Bulletin A300-53-6182, dated November 17,
2015.
Airbus Service Bulletin A310-53-2142, dated November 17,
2015.
This service information describes procedures for replacement of
the aft hinge bolt assemblies in the left and right NLG aft doors, with
new aft hinge bolt assemblies. These documents are distinct since they
apply to different airplane models and configurations.
We also reviewed the following Airbus service information.
Airbus Service Bulletin A300-53-0397, dated January 18,
2016.
Airbus Service Bulletin A300-53-6186, dated January 18,
2016.
Airbus Service Bulletin A310-53-2144, dated January 18,
2016.
This service information describes procedures for replacement of
the aft hinge bolt assemblies in the left and right NLG aft doors, with
new aft hinge bolt assemblies. The replacement includes an inspection
to verify if the proper bolt part number was installed and repair if
the proper bolt part number was not installed. These documents are
distinct since they apply to different airplane models and
configurations.
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
We estimate that this AD affects 157 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Replacement........................ 9 work-hours x $85 per hour $2,000 $2,765 $434,105
= $765.
----------------------------------------------------------------------------------------------------------------
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
[[Page 39354]]
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 to
the Director of the System Oversight Division.
Regulatory Findings
We 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. 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):
2017-16-06 Airbus: Amendment 39-18983; Docket No. FAA-2016-9052;
Product Identifier 2016-NM-080-AD.
(a) Effective Date
This AD is effective September 22, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus airplanes identified in paragraphs
(c)(1) through (c)(6) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R and F4-622R airplanes.
(5) Model A300 C4-605R Variant F airplanes.
(6) Model A310-203, -204, -221, -222, -304, -322, -324, and -325
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of failure of an aft hinge bolt
assembly in the nose landing gear (NLG) aft doors. We are issuing
this AD to prevent failure of an aft hinge bolt assembly in an NLG
aft door while the airplane is in flight, which could lead to an in-
flight loss of an NLG aft door, and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Replacement of Aft Hinge Bolt Assemblies Having Part Number (P/N)
A53612600000
Before the accumulation of 10,000 total flight cycles since
first flight of the airplane, or within 2,000 flight cycles after
the effective date of this AD, whichever occurs later: Replace each
aft hinge bolt assembly having P/N A53612600000 on the left and
right NLG aft doors, with a new hinge bolt assembly having P/N
A53612713000, in accordance with the Accomplishment Instructions of
the applicable service information identified in paragraph (g)(1),
(g)(2), or (g)(3) of this AD.
(1) Airbus Service Bulletin A300-53-0396, dated November 25,
2015.
(2) Airbus Service Bulletin A310-53-2142, dated November 17,
2015.
(3) Airbus Service Bulletin A300-53-6182, dated November 17,
2015.
(h) Replacement of Aft Hinge Bolt Assemblies Having P/N A53612713000
Within 10,000 flight cycles after modification of an airplane as
required by paragraph (g) of this AD: Replace each aft hinge bolt
assembly having P/N A53612713000 on the left and right NLG aft
doors, with a new aft hinge bolt assembly having P/N A53612713000 on
the left and right NLG aft doors, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, except
where the service information specified in paragraph (h)(1), (h)(2),
or (h)(3) of this AD specifies to contact Airbus for instructions,
before further flight repair using the procedure in paragraph (k)(2)
of this AD. Repeat the replacement thereafter at intervals not to
exceed 10,000 flight cycles.
(1) Airbus Service Bulletin A300-53-0397, dated January 18,
2016.
(2) Airbus Service Bulletin A310-53-2144, dated January 18,
2016.
(3) Airbus Service Bulletin A300-53-6186, dated January 18,
2016.
(i) Parts Installation Prohibition (P/N A53612600000)
After modification of an airplane NLG aft door as required by
paragraph (g) of this AD, do not install an aft hinge bolt assembly
having P/N A53612600000 on any NLG aft door of that airplane.
(j) Parts Installation Limitation (P/N A53612713000)
After removal of an aft hinge bolt assembly having P/N
A53612713000 from an airplane NLG aft door, as required by paragraph
(h) of this AD, do not install an aft hinge bolt assembly having
that part number on that airplane unless it is a new aft hinge bolt
assembly.
(k) 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 (l)(2) of this AD. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@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's EASA Design Organization Approval
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in
[[Page 39355]]
an airworthy condition. Any substitutions or changes to procedures
or tests identified as RC require approval of an AMOC.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0100, dated May 24, 2016,
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-2016-9052.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone
425-227-2125; fax 425-227-1149.
(m) 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.
(i) Airbus Service Bulletin A300-53-0396, dated November 25,
2015.
(ii) Airbus Service Bulletin A300-53-0397, dated January 18,
2016.
(iii) Airbus Service Bulletin A300-53-6182, dated November 17,
2015.
(iv) Airbus Service Bulletin A300-53-6186, dated January 18,
2016.
(v) Airbus Service Bulletin A310-53-2142, dated November 17,
2015.
(vi) Airbus Service Bulletin A310-53-2144, dated January 18,
2016.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 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.
(4) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
(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/ibr-locations.html.
Issued in Renton, Washington, on July 26, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-16359 Filed 8-17-17; 8:45 am]
BILLING CODE 4910-13-P