Airworthiness Directives; Airbus Airplanes, 24690-24694 [2018-11421]
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Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules
(a) Comments Due Date
We must receive comments by July 16,
2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 747–8 and 747–8F series
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 35, Oxygen.
(e) Unsafe Condition
This AD was prompted by a report that
flightcrew oxygen masks did not function as
designed during flight testing. We are issuing
this AD to address flightcrew oxygen masks/
regulators that do not deploy correctly,
which could result in a delay for the
flightcrew to put on the masks, which may
lead to hypoxia and loss of useful
consciousness, potentially resulting in loss of
control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
For airplanes with an original certificate of
airworthiness, or an original export
certificate of airworthiness, issued on or
before the effective date of this AD: Within
72 months after the effective date of this AD,
inspect for oxygen mask/regulator part
number (P/N) MLD20–626–1 and stowage
box P/N MXP806–1. If any oxygen mask/
regulator P/N MLD20–626–1 or stowage box
P/N MXP806–1 is found, within 72 months
after the effective date of this AD, do all
applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–35–2133, Revision 1,
dated November 1, 2017, except as provided
by paragraph (h) of this AD. A review of
airplane maintenance records is acceptable in
lieu of the part number inspection if the part
numbers of the oxygen mask/regulator and
stowage box can be conclusively determined
from that review.
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(h) Exceptions to Service Information
Specifications
Where Boeing Special Attention Service
Bulletin 747–35–2133, Revision 1, dated
November 1, 2017, refers to or specifies
installing a new (or changed) part, for this
AD, a new or serviceable (or changed) part
is acceptable.
(i) Parts Installation Limitation
(1) For airplanes with an original certificate
of airworthiness, or an original export
certificate of airworthiness, issued on or
before the effective date of this AD: As of the
effective date of this AD, no person may
install an oxygen mask/regulator P/N
MLD20–626–1 on any airplane, except that
prior to 72 months after the effective date of
this AD, installation of P/N MLD20–626–1 is
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acceptable for unscheduled maintenance as a
replacement only for another P/N MLD20–
626–1 and only into a stowage box P/N
MXP806–1. If an oxygen mask/regulator
having a part number other than P/N
MLD20–626–1 is installed, it may not be
replaced with P/N MLD20–626–1. For the
purposes of this AD, unscheduled
maintenance is defined as maintenance that
was not planned for or scheduled in advance,
such as changing a defective or unserviceable
oxygen mask at dispatch.
(2) For airplanes with an original certificate
of airworthiness or an original export
certificate of airworthiness issued after the
effective date of this AD: As of the effective
date of this AD, no person may install oxygen
mask/regulator P/N MLD20–626–1, on any
airplane.
(3) For all airplanes: As of the effective
date of this AD, no person may install oxygen
mask/regulator P/N MLD20–726–1, in
combination with any stowage box part
number that is not P/N MXP806–7, on any
airplane.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (h) of
this AD: For service information that
contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(4)(ii)
of this AD apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled 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 RC steps,
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including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(k) Related Information
(1) For more information about this AD,
contact Susan L. Monroe, Aerospace
Engineer, Cabin Safety and Environmental
Systems Section, FAA, Seattle ACO Branch,
2200 South 216th Street, Des Moines, WA
98198; phone and fax: 206–231–3570; email:
susan.l.monroe@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Standards Branch, 2200 South
216th St., Des Moines, WA. For information
on the availability of this material at the
FAA, call 206–231–3195.
Issued in Des Moines, Washington, on May
21, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–11426 Filed 5–29–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0455; Product
Identifier 2017–NM–121–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 98–18–24,
which applies to certain Airbus Model
A320 series airplanes. AD 98–18–24
requires repetitive inspections to detect
cracking in the inner flange of a certain
door frame, and corrective actions, if
necessary. AD 98–18–24 also provides
an optional terminating action for the
repetitive inspections. Since we issued
AD 98–18–24, it has been determined
that the compliance times for the
repetitive inspections must be reduced.
This proposed AD would continue to
require the repetitive inspections of the
inner flange of a certain door frame,
with reduced repetitive inspection
intervals, and corrective action if
necessary. We are proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
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Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules
We must receive comments on
this proposed AD by July 16, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, 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
Standards Branch, 2200 South 216th St.,
Des Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195.
DATES:
Examining the AD Docket
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You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0455; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA; 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2018–0455; Product Identifier 2017–
NM–121–AD’’ at the beginning of your
comments. We specifically invite
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comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We issued AD 98–18–24, Amendment
39–10740 (63 FR 49272, September 15,
1998) (‘‘AD 98–18–24’’), for certain
A320 series airplanes. AD 98–18–24 was
prompted by the results of a fatigue test
on simulated flights which revealed
cracks on the inner flange of door frame
66 at stringers 18 and 20. The cracks
were located in the gusset plate
attachment holes and were hidden by
the gusset plates. AD 98–18–24 requires
repetitive inspections to detect cracking
in the inner flange of door frame 66, and
corrective actions if necessary. AD 98–
18–24 also provides an optional
terminating action for the repetitive
inspections. We issued AD 98–18–24 to
detect and correct fatigue cracking in
the inner flange of door frame 66, which
could result in reduced structural
integrity of the airplane.
Since we issued AD 98–18–24, based
on the results from a full scale fatigue
test, it has been determined that the
repetitive inspection intervals must be
reduced.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2017–0128, dated July 24,
2017 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A320–211 and A320–231
airplanes. The MCAI states:
During fatigue test on simulated flights,
cracks developed on the inner flange of door
frame 66 at stringer 18 and 20 positions.
These cracks were located in the gusset plate
attachment holes and were hidden by the
plates.
This condition, if not detected and
corrected, could affect the structural integrity
of the fuselage.
To address this potential unsafe condition,
Airbus issued Service Bulletin (SB) A320–
53–1071, later revised, to provide
instructions to inspect and repair the gusset
plate attachment holes at frame 66, at
stringers 18, 20 and 22 both left hand (LH)
and right hand (RH) side of the fuselage
(hereafter collectively referred to as ‘‘the
attachment holes’’ in this [EASA] AD), and
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[Airbus] SB A320–53–1072, providing
instructions for reworking of the attachment
holes.
Consequently, DGAC France issued
[French] AD 1996–234–087, later revised
[which corresponds to FAA AD 98–18–24],
requiring repetitive inspections and,
depending on findings, repair of the
attachment holes, and including reference to
a reworking procedure, which constitutes
optional terminating action for the repetitive
inspections of the attachment holes.
Since that [French] AD was issued, based
on results from a full scale fatigue test, it was
determined that the inspection intervals must
be reduced. Airbus issued SB A320–53–1071
Revision 03, modifying the inspection
threshold and intervals, and not changing the
inspection instructions.
For the reason described above, this
[EASA] AD retains the requirement of DGAC
France AD 1996–234–087 R1, which is
superseded, and requires reduction of the
repetitive inspection interval.
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–
0455.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–53–1071, Revision 03, dated July
20, 2017. This service information
describes procedures for detailed
inspections of the gusset plate
attachment holes at door frame 66 for
cracking and corrective action.
Airbus also issued Service Bulletin
A320–53–1072, Revision 02, dated May
5, 2016. This service information
describes procedures for modification of
the gusset frame attachment at door
frame 66.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD
affects 3 airplanes of U.S. registry.
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The actions required by AD 98–18–24,
and retained in this proposed AD take
about 8 work-hours per product, at an
average labor rate of $85 per work-hour.
Based on these figures, the estimated
cost of the actions that are required by
AD 98–18–24 is $680 per product.
We estimate that it would take about
19 work-hours per product to comply
with the basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Based on these
figures, we estimate the cost of this
proposed AD on U.S. operators to be
$4,845, or $1,615 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
In addition, we estimate that the
optional terminating action would take
about 20 work-hours per product, at an
average labor rate of $85 per work-hour.
Required parts costs would be about
$60. Based on these figures, the
estimated cost of the optional
terminating action would be $1,760 per
product.
We also estimate that it would take
about 1 work-hour per product to
comply with the proposed reporting
requirement in this proposed AD. The
average labor rate is $85 per hour. Based
on these figures, we estimate the cost of
reporting the inspection results on U.S.
operators to be $255, or $85 per product.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW, Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
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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
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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
98–18–24 Amendment 39–10740 (63 FR
49272, September 15, 1998), and adding
the following new AD:
■
Airbus: Docket No. FAA–2018–0455; Product
Identifier 2017–NM–121–AD.
(a) Comments Due Date
We must receive comments by July 16,
2018.
(b) Affected ADs
This AD replaces AD 98–18–24
Amendment 39–10740 (63 FR 49272,
September 15, 1998) (‘‘AD 98–18–24’’).
(c) Applicability
This AD applies to Airbus Model A320–
211 and Model A320–231 airplanes,
certificated in any category, serial numbers
0029, 0045, 0046, 0049 through 0057
inclusive, 0059, 0064, and 0065.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of
cracks on the inner flange of door frame 66
at stringer 18 and 20 positions and by the
results of a full scale fatigue test that
indicated the intervals for the repetitive
inspections required by AD 98–18–24 must
be reduced. We are issuing this AD to detect
and correct fatigue cracking in the inner
flange of door frame 66, which could result
in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Eddy Current Inspection, With
No Changes
This paragraph restates the requirements of
paragraph (a) of AD 98–18–24, with no
changes. For Model A320 series airplanes on
which Airbus Modification 21778 (reference
Airbus Service Bulletin A320–53–1072,
dated November 7, 1995, as revised by
Change Notice 0A, dated July 5, 1996) has
not been accomplished: Prior to the
accumulation of 20,000 total flight cycles, or
within 1 year after October 20, 1998 (the
effective date of AD 98–18–24), whichever
occurs later: Perform a rotating probe eddy
current inspection to detect cracking around
the edges of the gusset plate attachment holes
of the inner flange of door frame 66, left and
right, at stringer positions P18, P20, and P22,
in accordance with Airbus Service Bulletin
A320–53–1071, dated November 7, 1995, as
revised by Change Notice 0A, dated July 5,
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Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules
(h) Retained Optional Terminating Action,
With No Changes
This paragraph restates the optional
terminating action of paragraph (b) of AD 98–
18–24, with no changes. Modification of the
gusset plate attachment holes of the inner
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(j) Corrective Actions
(1) If, during any inspection required by
paragraph (i) of this AD, any crack is found
on a gusset plate attachment hole: Before
further flight, repair the affected attachment
hole, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1071, Revision 03,
dated July 20, 2017, except as required by
paragraph (n) of this AD.
(2) If, during any inspection required by
paragraph (i) of this AD, any crack is found
on any other hole of the gusset plate: Before
further flight, contact the Manager,
International Section, Transport Standards
Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA); for
approved repair instructions and accomplish
those instructions accordingly. If approved
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flange of door frame 66, left and right (Airbus
Modification 21778), in accordance with
Airbus Service Bulletin A320–53–1072,
dated November 7, 1995, as revised by
Change Notice 0A, dated July 5, 1996,
constitutes terminating action for the
repetitive inspection requirements of
paragraph (g) of this AD.
(i) New Requirement of This AD: Repetitive
Inspections
At the applicable compliance time
specified in figure 1 to paragraph (i) of this
AD, do a rotating probe eddy current
inspection to detect cracking around the
edges of the gusset plate attachment holes of
the inner flange of door frame 66, left and
right, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1071, Revision 03,
dated July 20, 2017. Repeat the inspection
thereafter at intervals not to exceed 10,900
flight cycles.
by the DOA, the approval must include the
DOA-authorized signature.
terminates the inspections required by
paragraph (g) of this AD.
(k) Terminating Action for This AD
(l) Optional Modification
(1) Repair of an attachment hole area as
required by paragraph (j)(1) of this AD
terminates the repetitive inspections required
by paragraph (i) of this AD for that
attachment hole area on that airplane only.
(2) Repair of any other hole of the gusset
plate, as required by paragraph (j)(2) of this
AD, does not terminate the repetitive
inspections required by paragraph (i) of this
AD for that airplane, unless specified
otherwise in the repair instructions provided
by the Manager, International Section,
Transport Standards Branch, FAA; or the
EASA; or Airbus’s EASA DOA.
(3) Accomplishing the initial inspection
required by paragraph (i) of this AD
Modification of the gusset plate attachment
holes of the inner flange of door frame 66, left
and right, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1072, Revision 02,
dated May 5, 2016, terminates the repetitive
inspections required by paragraph (i) of this
AD for that airplane.
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(m) Reporting
Report the results of the inspection
required by paragraph (i) of this AD that are
done on or after the effective date of this AD
to Airbus Service Bulletin Reporting Online
Application on Airbus World (https://
w3.airbus.com/), or submit the results to
Airbus in accordance with the instructions of
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1996. If any crack is detected, prior to further
flight, repair in accordance with a method
approved by the Manager, International
Section, Transport Standards Branch, FAA.
Repeat the inspection thereafter at intervals
not to exceed 20,000 flight cycles.
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Airbus Service Bulletin A320–53–1071,
Revision 03, dated July 20, 2017. Submit the
report within 30 days after accomplishing the
inspection required by paragraph (i) of this
AD. The report must include the inspection
results, a description of any discrepancies
found, the airplane serial number, and the
number of landings and flight hours on the
airplane. If operators have reported findings
as part of obtaining any corrective actions
approved by the EASA DOA, operators are
not required to report those findings as
specified in this paragraph.
(n) Service Information Exception
Where Airbus Service Bulletin A320–53–
1071, Revision 03, dated July 20, 2017,
specifies to contact Airbus for appropriate
action, and specifies that action as ‘‘RC’’
(Required for Compliance): Before further
flight, accomplish corrective actions in
accordance with the procedures specified in
paragraph (q)(2) of this AD.
(o) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (i) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–53–1071, Revision 01, dated
July 4, 2002; or Airbus Service Bulletin
A320–53–1071, Revision 02, dated May 5,
2016.
(2) This paragraph provides credit for
actions identified in paragraph (l) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–53–1072, dated November 7,
1995, as revised by Change Notice 0A, dated
July 5, 1996; or Airbus Service Bulletin
A320–53–1072, Revision 01, dated July 4,
2002.
sradovich on DSK3GMQ082PROD with PROPOSALS
(p) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 1 hour per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW, Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
(q) Other FAA AD Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
VerDate Sep<11>2014
16:20 May 29, 2018
Jkt 244001
Office, as appropriate. If sending information
directly to the International Section, 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.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(ii) AMOCs approved previously for AD
98–18–24 are approved as AMOCs for the
corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized 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
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.
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0128, dated July 24, 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–2018–0455.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA; 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
(3) 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 service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
Issued in Des Moines, Washington, on May
21, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–11421 Filed 5–29–18; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0453; Product
Identifier 2018–NM–028–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model DHC–8–400
series airplanes. This proposed AD was
prompted by reports of the nose landing
gear (NLG) locking in a partially
extended position due to loose bushings
on the lock link of the NLG locking
mechanism. This proposed AD would
require inspecting the bushings and the
lower lock link of the NLG for
discrepancies, and corrective actions if
necessary. We are proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by July 16, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5,
Canada; telephone: 416–375–4000; fax:
416–375–4539; email: thd.qseries@
aero.bombardier.com; internet: https://
www.bombardier.com. You may view
this service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
DATES:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
E:\FR\FM\30MYP1.SGM
30MYP1
]]>Agencies
[Federal Register Volume 83, Number 104 (Wednesday, May 30, 2018)]
[Proposed Rules]
[Pages 24690-24694]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11421]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0455; Product Identifier 2017-NM-121-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 98-18-24,
which applies to certain Airbus Model A320 series airplanes. AD 98-18-
24 requires repetitive inspections to detect cracking in the inner
flange of a certain door frame, and corrective actions, if necessary.
AD 98-18-24 also provides an optional terminating action for the
repetitive inspections. Since we issued AD 98-18-24, it has been
determined that the compliance times for the repetitive inspections
must be reduced. This proposed AD would continue to require the
repetitive inspections of the inner flange of a certain door frame,
with reduced repetitive inspection intervals, and corrective action if
necessary. We are proposing this AD to address the unsafe condition on
these products.
[[Page 24691]]
DATES: We must receive comments on this proposed AD by July 16, 2018.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, 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 [email protected]; internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195.
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-
0455; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA; 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2018-0455;
Product Identifier 2017-NM-121-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed
AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We issued AD 98-18-24, Amendment 39-10740 (63 FR 49272, September
15, 1998) (``AD 98-18-24''), for certain A320 series airplanes. AD 98-
18-24 was prompted by the results of a fatigue test on simulated
flights which revealed cracks on the inner flange of door frame 66 at
stringers 18 and 20. The cracks were located in the gusset plate
attachment holes and were hidden by the gusset plates. AD 98-18-24
requires repetitive inspections to detect cracking in the inner flange
of door frame 66, and corrective actions if necessary. AD 98-18-24 also
provides an optional terminating action for the repetitive inspections.
We issued AD 98-18-24 to detect and correct fatigue cracking in the
inner flange of door frame 66, which could result in reduced structural
integrity of the airplane.
Since we issued AD 98-18-24, based on the results from a full scale
fatigue test, it has been determined that the repetitive inspection
intervals must be reduced.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2017-0128, dated July 24, 2017 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A320-211 and A320-231 airplanes. The MCAI states:
During fatigue test on simulated flights, cracks developed on
the inner flange of door frame 66 at stringer 18 and 20 positions.
These cracks were located in the gusset plate attachment holes and
were hidden by the plates.
This condition, if not detected and corrected, could affect the
structural integrity of the fuselage.
To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A320-53-1071, later revised, to provide
instructions to inspect and repair the gusset plate attachment holes
at frame 66, at stringers 18, 20 and 22 both left hand (LH) and
right hand (RH) side of the fuselage (hereafter collectively
referred to as ``the attachment holes'' in this [EASA] AD), and
[Airbus] SB A320-53-1072, providing instructions for reworking of
the attachment holes.
Consequently, DGAC France issued [French] AD 1996-234-087, later
revised [which corresponds to FAA AD 98-18-24], requiring repetitive
inspections and, depending on findings, repair of the attachment
holes, and including reference to a reworking procedure, which
constitutes optional terminating action for the repetitive
inspections of the attachment holes.
Since that [French] AD was issued, based on results from a full
scale fatigue test, it was determined that the inspection intervals
must be reduced. Airbus issued SB A320-53-1071 Revision 03,
modifying the inspection threshold and intervals, and not changing
the inspection instructions.
For the reason described above, this [EASA] AD retains the
requirement of DGAC France AD 1996-234-087 R1, which is superseded,
and requires reduction of the repetitive inspection interval.
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-
0455.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-53-1071, Revision 03, dated
July 20, 2017. This service information describes procedures for
detailed inspections of the gusset plate attachment holes at door frame
66 for cracking and corrective action.
Airbus also issued Service Bulletin A320-53-1072, Revision 02,
dated May 5, 2016. This service information describes procedures for
modification of the gusset frame attachment at door frame 66.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 3 airplanes of U.S.
registry.
[[Page 24692]]
The actions required by AD 98-18-24, and retained in this proposed
AD take about 8 work-hours per product, at an average labor rate of $85
per work-hour. Based on these figures, the estimated cost of the
actions that are required by AD 98-18-24 is $680 per product.
We estimate that it would take about 19 work-hours per product to
comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $4,845, or $1,615
per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
In addition, we estimate that the optional terminating action would
take about 20 work-hours per product, at an average labor rate of $85
per work-hour. Required parts costs would be about $60. Based on these
figures, the estimated cost of the optional terminating action would be
$1,760 per product.
We also estimate that it would take about 1 work-hour per product
to comply with the proposed reporting requirement in this proposed AD.
The average labor rate is $85 per hour. Based on these figures, we
estimate the cost of reporting the inspection results on U.S. operators
to be $255, or $85 per product.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
98-18-24 Amendment 39-10740 (63 FR 49272, September 15, 1998), and
adding the following new AD:
Airbus: Docket No. FAA-2018-0455; Product Identifier 2017-NM-121-AD.
(a) Comments Due Date
We must receive comments by July 16, 2018.
(b) Affected ADs
This AD replaces AD 98-18-24 Amendment 39-10740 (63 FR 49272,
September 15, 1998) (``AD 98-18-24'').
(c) Applicability
This AD applies to Airbus Model A320-211 and Model A320-231
airplanes, certificated in any category, serial numbers 0029, 0045,
0046, 0049 through 0057 inclusive, 0059, 0064, and 0065.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of cracks on the inner flange
of door frame 66 at stringer 18 and 20 positions and by the results
of a full scale fatigue test that indicated the intervals for the
repetitive inspections required by AD 98-18-24 must be reduced. We
are issuing this AD to detect and correct fatigue cracking in the
inner flange of door frame 66, which could result in reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Eddy Current Inspection, With No Changes
This paragraph restates the requirements of paragraph (a) of AD
98-18-24, with no changes. For Model A320 series airplanes on which
Airbus Modification 21778 (reference Airbus Service Bulletin A320-
53-1072, dated November 7, 1995, as revised by Change Notice 0A,
dated July 5, 1996) has not been accomplished: Prior to the
accumulation of 20,000 total flight cycles, or within 1 year after
October 20, 1998 (the effective date of AD 98-18-24), whichever
occurs later: Perform a rotating probe eddy current inspection to
detect cracking around the edges of the gusset plate attachment
holes of the inner flange of door frame 66, left and right, at
stringer positions P18, P20, and P22, in accordance with Airbus
Service Bulletin A320-53-1071, dated November 7, 1995, as revised by
Change Notice 0A, dated July 5,
[[Page 24693]]
1996. If any crack is detected, prior to further flight, repair in
accordance with a method approved by the Manager, International
Section, Transport Standards Branch, FAA. Repeat the inspection
thereafter at intervals not to exceed 20,000 flight cycles.
(h) Retained Optional Terminating Action, With No Changes
This paragraph restates the optional terminating action of
paragraph (b) of AD 98-18-24, with no changes. Modification of the
gusset plate attachment holes of the inner flange of door frame 66,
left and right (Airbus Modification 21778), in accordance with
Airbus Service Bulletin A320-53-1072, dated November 7, 1995, as
revised by Change Notice 0A, dated July 5, 1996, constitutes
terminating action for the repetitive inspection requirements of
paragraph (g) of this AD.
(i) New Requirement of This AD: Repetitive Inspections
At the applicable compliance time specified in figure 1 to
paragraph (i) of this AD, do a rotating probe eddy current
inspection to detect cracking around the edges of the gusset plate
attachment holes of the inner flange of door frame 66, left and
right, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017.
Repeat the inspection thereafter at intervals not to exceed 10,900
flight cycles.
[GRAPHIC] [TIFF OMITTED] TP30MY18.000
(j) Corrective Actions
(1) If, during any inspection required by paragraph (i) of this
AD, any crack is found on a gusset plate attachment hole: Before
further flight, repair the affected attachment hole, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-53-1071, Revision 03, dated July 20, 2017, except as required
by paragraph (n) of this AD.
(2) If, during any inspection required by paragraph (i) of this
AD, any crack is found on any other hole of the gusset plate: Before
further flight, contact the Manager, International Section,
Transport Standards Branch, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA);
for approved repair instructions and accomplish those instructions
accordingly. If approved by the DOA, the approval must include the
DOA-authorized signature.
(k) Terminating Action for This AD
(1) Repair of an attachment hole area as required by paragraph
(j)(1) of this AD terminates the repetitive inspections required by
paragraph (i) of this AD for that attachment hole area on that
airplane only.
(2) Repair of any other hole of the gusset plate, as required by
paragraph (j)(2) of this AD, does not terminate the repetitive
inspections required by paragraph (i) of this AD for that airplane,
unless specified otherwise in the repair instructions provided by
the Manager, International Section, Transport Standards Branch, FAA;
or the EASA; or Airbus's EASA DOA.
(3) Accomplishing the initial inspection required by paragraph
(i) of this AD terminates the inspections required by paragraph (g)
of this AD.
(l) Optional Modification
Modification of the gusset plate attachment holes of the inner
flange of door frame 66, left and right, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1072,
Revision 02, dated May 5, 2016, terminates the repetitive
inspections required by paragraph (i) of this AD for that airplane.
(m) Reporting
Report the results of the inspection required by paragraph (i)
of this AD that are done on or after the effective date of this AD
to Airbus Service Bulletin Reporting Online Application on Airbus
World (https://w3.airbus.com/), or submit the results to Airbus in
accordance with the instructions of
[[Page 24694]]
Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20,
2017. Submit the report within 30 days after accomplishing the
inspection required by paragraph (i) of this AD. The report must
include the inspection results, a description of any discrepancies
found, the airplane serial number, and the number of landings and
flight hours on the airplane. If operators have reported findings as
part of obtaining any corrective actions approved by the EASA DOA,
operators are not required to report those findings as specified in
this paragraph.
(n) Service Information Exception
Where Airbus Service Bulletin A320-53-1071, Revision 03, dated
July 20, 2017, specifies to contact Airbus for appropriate action,
and specifies that action as ``RC'' (Required for Compliance):
Before further flight, accomplish corrective actions in accordance
with the procedures specified in paragraph (q)(2) of this AD.
(o) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (i) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-53-
1071, Revision 01, dated July 4, 2002; or Airbus Service Bulletin
A320-53-1071, Revision 02, dated May 5, 2016.
(2) This paragraph provides credit for actions identified in
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-53-
1072, dated November 7, 1995, as revised by Change Notice 0A, dated
July 5, 1996; or Airbus Service Bulletin A320-53-1072, Revision 01,
dated July 4, 2002.
(p) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 1 hour per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(q) Other FAA AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (r)(2) of this AD. Information
may be emailed to: [email protected]ov.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(ii) AMOCs approved previously for AD 98-18-24 are approved as
AMOCs for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or the 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 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.
(r) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0128, dated July 24, 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-2018-0455.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA; 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3223.
(3) 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 [email protected]; internet https://www.airbus.com. You may view this service information at the FAA,
Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA,
call 206-231-3195.
Issued in Des Moines, Washington, on May 21, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-11421 Filed 5-29-18; 8:45 am]
BILLING CODE 4910-13-P
