Airworthiness Directives; Airbus Airplanes, 38091-38096 [2018-16497]
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Federal Register / Vol. 83, No. 150 / Friday, August 3, 2018 / Proposed Rules
applicable service information specified in
paragraphs (i)(1) through (i)(7) of this AD.
(1) Airbus Service Bulletin A330–29–3131,
dated August 11, 2017.
(2) Airbus Service Bulletin A330–29–3132,
dated August 11, 2017.
(3) Airbus Service Bulletin A330–29–3133,
dated August 11, 2017.
(4) Airbus Service Bulletin A340–29–4099,
dated August 11. 2017.
(5) Airbus Service Bulletin A340–29–4100,
dated August 11, 2017.
(6) Airbus Service Bulletin A340–29–4101,
dated August 11, 2017.
(7) Airbus Service Bulletin A340–29–5026,
dated August 11, 2017.
(j) Part Re-identification
(1) For Group 1 airplanes: Concurrently
with the PRV replacement required by
paragraph (i) of this AD, re-identify the part
numbers of affected HRs as specified in table
1 to paragraphs (g), (h), (i), and (j) of this AD,
in accordance with the applicable service
information specified in paragraphs (i)(1)
through (i)(7) of this AD.
(2) For Group 2 airplanes: At the applicable
time specified in table 1 to paragraphs (g),
(h), (i), and (j) of this AD, re-identify the part
numbers of affected PRVs and HRs, in
accordance with the applicable service
information specified in paragraphs (i)(1)
through (i)(7) of this AD.
(k) Terminating Action
Replacement of all affected PRVs on an
airplane, as required by paragraph (i) of this
AD, terminates all requirements of AD 2017–
01–08 for that airplane.
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(l) Parts Installation Prohibition
(1) For Group 1 airplanes: After
replacement of all affected parts as required
by paragraph (i) of this AD, do not install any
affected PRV.
(2) For Group 2 airplanes: As of the
effective date of this AD, do not install any
affected PRV.
(m) 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 Branch, send it
to the attention of the person identified in
paragraph (n)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
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Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the 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
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0064, dated March 23, 2018, for related
information. This MCAI may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2018–0704.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax: 206–231–3229.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, Rond Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
telephone: +33 5 61 93 36 96; fax: +33 5 61
93 45 80; email: airworthiness.A330-A340@
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 July
25, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–16574 Filed 8–2–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0641; Product
Identifier 2018–NM–032–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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38091
Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to supersede
Airworthiness Directive (AD) 2017–22–
07, which applies to certain Airbus
Model A319 series airplanes; Model
A320–211, –212, –214, –231, –232, and
–233 airplanes; and Model A321–111,
–112, –131, –211, –212, –213, –231, and
–232 airplanes. AD 2017–22–07 requires
repetitive inspections of the frame forks,
and corrective actions if necessary. AD
2017–22–07 also includes optional
modifications that constitute
terminating action. Since we issued AD
2017–22–07, an evaluation was done by
the design approval holder (DAH)
indicating that the frame forks and outer
skin on the forward and aft cargo
compartment doors are subject to
widespread fatigue damage (WFD), and
a determination was made that a
modification of the frame forks must be
accomplished. This proposed AD would
require modifying certain forward and
aft cargo compartment doors, and
related investigative and corrective
actions. We are proposing this AD to
address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by September 17,
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, 2 Rond
Point Emile Dewoitine, 31700 Blagnac
Cedex, France; telephone: +33 5 61 93
36 96; fax: +33 5 61 93 44 51; email:
account.airworth-eas@airbus.com;
internet: https://www.airbus.com. 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.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
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www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0641; 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 NPRM, 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–
2018–0641; Product Identifier 2018–
NM–032–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.
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Discussion
Fatigue damage can occur locally, in
small areas or structural design details,
or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as WFD. It is
associated with general degradation of
large areas of structure with similar
structural details and stress levels. As
an airplane ages, WFD will likely occur,
and will certainly occur if the airplane
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is operated long enough without any
intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
We issued AD 2017–22–07,
Amendment 39–19087 (82 FR 56158,
November 28, 2017) (‘‘AD 2017–22–
07’’), for certain Airbus Model A319
series airplanes; Model A320–211, –212,
–214, –231, –232, and –233 airplanes;
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
AD 2017–22–07 requires repetitive
inspections of the frame forks, and
corrective actions if necessary. AD
2017–22–07 also includes optional
modifications that constitute
terminating action. AD 2017–22–07
resulted from a report of cracks on frame
forks and outer skin on the forward and
aft cargo compartment doors. We issued
AD 2017–22–07 to address cracks on the
frame forks and outer skin on the
forward and aft cargo compartment
doors, which could lead to reduced
structural integrity and failure of the
cargo compartment door, possible
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decompression of the airplane, and
injury to occupants.
Actions Since AD 2017–22–07 Was
Issued
Since we issued AD 2017–22–07, an
evaluation was done by the DAH
indicating that the frame forks and outer
skin on the forward and aft cargo
compartment doors are subject to WFD,
and a determination was made that a
modification of the frame forks must be
accomplished.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2018–0024, dated January 29,
2018 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A319 series airplanes; Model
A320–211, –212, –214, –216, –231,
–232, and –233 airplanes; and Model
A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes. The
MCAI states:
During full scale fatigue test, cracks were
found on frame forks and outer skin on
forward and aft cargo doors. To improve the
fatigue behaviour of the frame forks, Airbus
introduced modification (mod) 22948 in
production, and issued inspection Service
Bulletin (SB) A320–52–1032 and mod SB
A320–52–1042, both recommended. Since
those actions were taken, further improved
cargo compartment doors were introduced in
production through Airbus mod 26213, on
aeroplanes having [manufacturer serial
number] MSN 0759 and up.
In the frame of the Widespread Fatigue
Damage (WFD) study, it was determined that
repetitive inspection are necessary for aft and
forward cargo compartment doors on
aeroplanes that are in pre-mod 26213
configuration. Failure to detect cracks would
reduce the cargo door structural integrity.
This condition, if not detected and
corrected, could lead to cargo door failure,
possibly resulting in decompression of the
aeroplane and injury to occupants.
To address this unsafe condition, Airbus
issued SB A320–52–1171 to provide
instructions for repetitive special detailed
inspections (SDI). This SB was later revised
to correct the list of affected cargo doors.
Airbus also issued SB A320–52–1170,
introducing a door modification which
would allow terminating the repetitive
SDI[s].
Consequently, EASA issued AD 2016–0187
[which corresponds to FAA AD 2017–22–07]
to require repetitive SDI[s] of the affected
cargo doors and, depending on findings, the
accomplishment of applicable repairs. That
[EASA] AD also included reference to SB
A320–52–1170 as optional terminating
action.
Since that [EASA] AD was issued, further
investigations linked to the WFD analysis
highlighted that, to meet the WFD
requirements, it is necessary to require
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embodiment of the terminating action
modification.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2016–0187, which is superseded, and
requires modification of all affected cargo
doors, which constitutes terminating action
for the repetitive SDI[s] required by this
[EASA] AD.
The related investigative action is a
high frequency eddy current (HFEC)
rotating probe inspection for cracks.
Corrective actions include, among other
things, oversizing and cold-expanding
any affected holes and repair. 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–
0641.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Service Bulletin A320–52–1171,
Revision 02, dated April 10, 2017,
which describes procedures for
repetitive special detailed inspections of
all frame forks in the beam 4 area of any
affected door, and corrective actions.
• Service Bulletin A320–52–1042,
Revision 2, dated January 14, 1997,
which describes procedures for
modification of all affected forward and
aft cargo compartment doors.
Action
Modification .......................
Inspection ..........................
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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 these same
type designs.
replaced before WFD develops in
airplanes. Standard inspection
techniques cannot be relied on to detect
WFD before it becomes a hazard to
flight. We will not grant any extensions
of the compliance time to complete any
AD-mandated service bulletin related to
WFD without extensive new data that
would substantiate and clearly warrant
such an extension.
Paragraphs (j)(2) and (j)(3) of AD
2017–22–07 allowed an optional
terminating modification that could be
done at any time. This proposed AD
would still permit that optional
terminating modification, but with new
limitations on the compliance time, i.e.,
the optional modification must be done
on or after the accumulation of 21,700
flight cycles since first installation of
the door on an airplane in order to
terminate the repetitive inspections. The
repetitive inspections are not terminated
if the modification is done before the
accumulation of 21,700 flight cycles
since first installation of the door on an
airplane. These limitations match those
in EASA AD 2018–0024, dated January
29, 2018.
Explanation of Compliance Time
Costs of Compliance
The compliance time for the
replacement specified in this proposed
AD for addressing WFD was established
to ensure that discrepant structure is
We estimate that this proposed AD
affects 88 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
FAA’s Determination and Requirements
of This Proposed AD
Labor cost
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
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Cost on
U.S. operators
Parts cost
24 work-hours × $85 per
hour = $2,040.
25 work-hours × $85 per
hour = $2,125.
Authority for This Rulemaking
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• Service Bulletin A320–52–1170,
including Appendices 01 and 02, dated
September 5, 2016, which describes
procedures for modifying all affected
forward and aft cargo compartment
doors, including oversize and cold
working of riveting for all frame forks.
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.
Cost per product
Up to $240 ........................
Up to $2,280 .....................
Up to $200,640.
$0 ......................................
$2,125 ...............................
$187,000.
products identified in this rulemaking
action.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes 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
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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.
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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)
2017–22–07, Amendment 39–19087 (82
FR 56158, November 28, 2017), and
adding the following new AD:
■
Airbus: Docket No. FAA–2018–0641; Product
Identifier 2018–NM–032–AD.
(a) Comments Due Date
We must receive comments by September
17, 2018.
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(h) Retained Repetitive Special Detailed
Inspection of Frame Forks, With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2017–22–07, with no
changes. At the latest of the compliance
times listed in paragraphs (h)(1) through
(h)(4) of this AD: Do a special detailed
inspection of all frame forks in the beam 4
area of any affected door as defined in
paragraph (g) of this AD, in accordance with
the Accomplishment Instructions of Airbus
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(b) Affected ADs
This AD replaces AD 2017–22–07,
Amendment 39–19087 (82 FR 56158,
November 28, 2017) (‘‘AD 2017–22–07’’).
(c) Applicability
This AD applies to Airbus Model A319–
111, –112, –113, –114, –115, –131, –132, and
–133 airplanes; Model A320–211, –212, –214,
–216, –231, –232, and –233 airplanes; and
Model A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes, certificated
in any category, manufacturer serial numbers
through 0758 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
(e) Reason
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that the frame forks and outer skin on the
forward and aft cargo compartment doors are
subject to widespread fatigue damage (WFD),
and a determination that a modification of
the frame forks must be accomplished. We
Service Bulletin A320–52–1171, Revision 02,
dated April 10, 2017, except as specified in
paragraphs (l) and (m) of this AD. Repeat the
inspection thereafter at intervals not to
exceed 3,000 flight cycles. A review of the
airplane delivery or maintenance records is
acceptable to identify any affected door
installed on the airplane, provided that the
cargo compartment door part number can be
conclusively determined from that review.
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are issuing this AD to address cracks on the
frame forks and outer skin on the forward
and aft cargo compartment doors, which
could lead to reduced structural integrity and
failure of the cargo compartment door,
possible decompression of the airplane, and
injury to occupants.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Definition of Affected Door,
With No Changes
This paragraph restates the definition in
paragraph (g) of AD 2017–22–07, with no
changes. For the purpose of this AD, an
‘‘affected door’’ is a forward or aft cargo
compartment door, having any part number
listed in table 1 to paragraph (g) of this AD,
except a cargo compartment door on which
Airbus Service Bulletin A320–52–1042 or
Airbus Service Bulletin A320–52–1170 is
embodied.
(1) Before exceeding 37,500 flight cycles
since first installation of the door on an
airplane.
(2) Within 900 flight cycles after January 2,
2018 (the effective date of AD 2017–22–07),
without exceeding 41,950 flight cycles since
first installation of the door on an airplane.
(3) Within 50 flight cycles after January 2,
2018 (the effective date of AD 2017–22–07),
for a door having reached or exceeded 41,900
flight cycles since first installation on an
airplane.
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The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
Federal Register / Vol. 83, No. 150 / Friday, August 3, 2018 / Proposed Rules
(4) Within 3,000 flight cycles since the last
inspection of the door as specified in Airbus
Service Bulletin A320–52–1032.
(i) Retained Corrective Actions, With No
Changes
This paragraph restates the requirements of
paragraph (i) of AD 2017–22–07, with no
changes. If any crack is found during any
inspection required by paragraph (h) of this
AD, before further flight, do all applicable
corrective actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1171, Revision 02,
dated April 10, 2017, except as specified in
paragraphs (l) and (m) of this AD.
Accomplishment of applicable corrective
actions does not constitute terminating action
for the repetitive inspections.
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(j) Terminating Modification
Before the accumulation of 56,300 total
flight cycles, but not before the accumulation
of 21,700 total flight cycles since first
installation of the affected door on an
airplane: Modify all affected doors of an
airplane, including accomplishment of all
applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1170, including
Appendices 01 and 02, dated September 5,
2016. Accomplishing this modification
constitutes terminating action for the
repetitive inspections specified in paragraph
(h) of this AD for that airplane, provided that,
after modification, no affected door is reinstalled on that airplane.
(k) Retained Optional Terminating Action,
With Changes Related to Compliance
This paragraph restates the requirements of
paragraph (j) of AD 2017–22–07, with
changes related to compliance.
(1) Modification of all affected doors of an
airplane before the effective date of this AD,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1042, Revision 2, dated January 14, 1997,
constitutes terminating action for the
repetitive inspections specified in paragraph
(h) of this AD and a method of compliance
for the modification required by paragraph (j)
of this AD, for that airplane, provided that,
after modification, no affected door is reinstalled on that airplane. On or after the
effective date of this AD, the modification
required by paragraph (j) of this AD must be
done.
(2) Modification of all affected doors of an
airplane including accomplishment of all
applicable related investigative and
corrective actions, if done before the effective
date of this AD in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1170, dated
September 5, 2016, except as specified in
paragraph (l) of this AD, constitutes
terminating action for the repetitive
inspections specified in paragraph (h) of this
AD and a method of compliance for the
modification required by paragraph (j) of this
AD, for that airplane, provided that, after
modification, no affected door is re-installed
on that airplane. On or after the effective date
of this AD, the modification required by
paragraph (j) of this AD must be done.
VerDate Sep<11>2014
18:01 Aug 02, 2018
Jkt 244001
(3) Modification of all affected doors on an
airplane, in case of finding damaged frame
forks, as specified in an Airbus Repair Design
Approval Sheet (RDAS), if done before the
effective date of this AD and done in
accordance with 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);
constitutes terminating action for the
repetitive inspection specified in paragraph
(h) of this AD and a method of compliance
for the modification required by paragraph (j)
of this AD, for that airplane, provided that,
after modification, no affected door is reinstalled on that airplane. On or after the
effective date of this AD, the modification
required by paragraph (j) of this AD must be
done.
(l) Retained Exception to Service
Information
This paragraph restates the requirements of
paragraph (k) of AD 2017–22–07, with no
changes. Where Airbus Service Bulletin
A320–52–1170, including Appendices 01
and 02, dated September 5, 2016; or Airbus
Service Bulletin A320–52–1171, Revision 02,
dated April 10, 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
(p)(2) of this AD.
(m) Retained No Reporting Requirement
This paragraph restates the requirements of
paragraph (l) of AD 2017–22–07, with no
changes. Although Airbus Service Bulletin
A320–52–1171, Revision 02, dated April 10,
2017, specifies to submit certain information
to the manufacturer, and specifies that action
as ‘‘RC,’’ this AD does not include that
requirement.
(n) Retained Credit for Previous Actions
This paragraph restates the requirements of
paragraph (m) of AD 2017–22–07, with no
changes.
(1) This paragraph provides credit for the
actions required by paragraphs (h) and (i) of
this AD, if those actions were performed
before January 2, 2018 (the effective date of
AD 2017–22–07), using Airbus Service
Bulletin A320–52–1171, dated October 29,
2015, provided that it can be conclusively
determined that any part number
D52371000018 was also inspected as
specified in paragraph (h) of this AD.
(2) This paragraph provides credit for the
actions required by paragraphs (h) and (i) of
this AD, if those actions were performed
before January 2, 2018 (the effective date of
AD 2017–22–07), using Airbus Service
Bulletin A320–52–1171, Revision 01, dated
September 5, 2016.
(o) Parts Installation Limitation
As of the effective date of this AD, no
person may install, on any airplane, an
affected door specified in paragraph (g) of
this AD, unless less than 56,300 flight cycles
have accumulated since first installation of
the door on an airplane, and unless the door
has been inspected in accordance with the
PO 00000
Frm 00023
Fmt 4702
Sfmt 4702
38095
requirements of paragraph (h) of this AD and
all applicable corrective actions have been
done in accordance with paragraph (i) of this
AD.
(p) 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 (p)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): Except
as specified in paragraphs (l) and (m) 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.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2018–0024, dated
January 29, 2018, for related information.
This MCAI may be found in the AD docket
on the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2018–0641.
(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, 2 Rond Point Emile Dewoitine,
31700 Blagnac Cedex, France; telephone: +33
E:\FR\FM\03AUP1.SGM
03AUP1
38096
Federal Register / Vol. 83, No. 150 / Friday, August 3, 2018 / Proposed Rules
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 July
24, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–16497 Filed 8–2–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
[Docket No. FAA–2018–0703; Product
Identifier 2018–NM–007–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 747–8 and 747–
8F series airplanes. This proposed AD
was prompted by reports of damaged
vapor seals, block seals, and heat shield
seals on the outboard pylons between
the engine strut and aft fairing. This
proposed AD would require installing
new aft fairing vapor seals, heatshield
seals, heatshield seal retainers, block
seals and outboard lateral restraint
access panels. We are proposing this AD
to address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by September 17,
2018.
SUMMARY:
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
amozie on DSK3GDR082PROD with PROPOSALS1
ADDRESSES:
VerDate Sep<11>2014
18:01 Aug 02, 2018
Jkt 244001
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, 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. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2018–0703.
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0703; 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 NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Christopher Baker, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3552; email: Christopher.R.Baker@
faa.gov.
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–
2018–0703; Product Identifier 2018–
NM–007–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of 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.
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
Discussion
We have received reports of damaged
vapor seals, block seals, and heat shield
seals on the outboard pylons between
the engine strut and aft fairing. Such
damage could allow flammable fluid
leakage out of the aft fairing. This
condition, if not addressed, could result
in an uncontrolled fire in the engine
strut.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 747–54A2247, dated August 3,
2017. This service information describes
procedures for installing new aft fairing
vapor seals, heatshield seals, heatshield
seal retainers, block seals, and outboard
lateral restraint access panels. 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
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require
accomplishment of the actions
identified as ‘‘RC’’ (required for
compliance) in the Accomplishment
Instructions of Boeing Alert Service
Bulletin 747–54A2247, dated August 3,
2017, described previously, except as
discussed under ‘‘Differences Between
this Proposed AD and the Service
Information,’’ and except for any
differences identified as exceptions in
the regulatory text of this proposed AD.
For information on the procedures
and compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0703.
Differences Between This Proposed AD
and the Service Information
The applicability in this proposed AD
does not refer to paragraph 1.A.,
‘‘Effectivity,’’ of Boeing Alert Service
Bulletin 747–54A2247, dated August 3,
2017. The service information does not
contain a comprehensive list of the
airplanes affected by the identified
unsafe condition because the spare parts
identified in paragraph (j) of this AD
have been determined to be rotable parts
that are capable of being installed on all
Model 747–8 and 747–8F series
airplanes. Therefore, the applicability of
E:\FR\FM\03AUP1.SGM
03AUP1
]]>Agencies
[Federal Register Volume 83, Number 150 (Friday, August 3, 2018)]
[Proposed Rules]
[Pages 38091-38096]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16497]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0641; Product Identifier 2018-NM-032-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) 2017-22-
07, which applies to certain Airbus Model A319 series airplanes; Model
A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2017-
22-07 requires repetitive inspections of the frame forks, and
corrective actions if necessary. AD 2017-22-07 also includes optional
modifications that constitute terminating action. Since we issued AD
2017-22-07, an evaluation was done by the design approval holder (DAH)
indicating that the frame forks and outer skin on the forward and aft
cargo compartment doors are subject to widespread fatigue damage (WFD),
and a determination was made that a modification of the frame forks
must be accomplished. This proposed AD would require modifying certain
forward and aft cargo compartment doors, and related investigative and
corrective actions. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by September 17,
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, 2 Rond Point Emile Dewoitine, 31700 Blagnac
Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51;
email: [email protected]; internet: https://www.airbus.com. 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://
[[Page 38092]]
www.regulations.gov by searching for and locating Docket No. FAA-2018-
0641; 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 NPRM, 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-2018-0641;
Product Identifier 2018-NM-032-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
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as WFD. It is associated with general
degradation of large areas of structure with similar structural details
and stress levels. As an airplane ages, WFD will likely occur, and will
certainly occur if the airplane is operated long enough without any
intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
We issued AD 2017-22-07, Amendment 39-19087 (82 FR 56158, November
28, 2017) (``AD 2017-22-07''), for certain Airbus Model A319 series
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes;
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes. AD 2017-22-07 requires repetitive inspections of the frame
forks, and corrective actions if necessary. AD 2017-22-07 also includes
optional modifications that constitute terminating action. AD 2017-22-
07 resulted from a report of cracks on frame forks and outer skin on
the forward and aft cargo compartment doors. We issued AD 2017-22-07 to
address cracks on the frame forks and outer skin on the forward and aft
cargo compartment doors, which could lead to reduced structural
integrity and failure of the cargo compartment door, possible
decompression of the airplane, and injury to occupants.
Actions Since AD 2017-22-07 Was Issued
Since we issued AD 2017-22-07, an evaluation was done by the DAH
indicating that the frame forks and outer skin on the forward and aft
cargo compartment doors are subject to WFD, and a determination was
made that a modification of the frame forks must be accomplished.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2018-0024, dated January 29, 2018 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232,
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes. The MCAI states:
During full scale fatigue test, cracks were found on frame forks
and outer skin on forward and aft cargo doors. To improve the
fatigue behaviour of the frame forks, Airbus introduced modification
(mod) 22948 in production, and issued inspection Service Bulletin
(SB) A320-52-1032 and mod SB A320-52-1042, both recommended. Since
those actions were taken, further improved cargo compartment doors
were introduced in production through Airbus mod 26213, on
aeroplanes having [manufacturer serial number] MSN 0759 and up.
In the frame of the Widespread Fatigue Damage (WFD) study, it
was determined that repetitive inspection are necessary for aft and
forward cargo compartment doors on aeroplanes that are in pre-mod
26213 configuration. Failure to detect cracks would reduce the cargo
door structural integrity.
This condition, if not detected and corrected, could lead to
cargo door failure, possibly resulting in decompression of the
aeroplane and injury to occupants.
To address this unsafe condition, Airbus issued SB A320-52-1171
to provide instructions for repetitive special detailed inspections
(SDI). This SB was later revised to correct the list of affected
cargo doors. Airbus also issued SB A320-52-1170, introducing a door
modification which would allow terminating the repetitive SDI[s].
Consequently, EASA issued AD 2016-0187 [which corresponds to FAA
AD 2017-22-07] to require repetitive SDI[s] of the affected cargo
doors and, depending on findings, the accomplishment of applicable
repairs. That [EASA] AD also included reference to SB A320-52-1170
as optional terminating action.
Since that [EASA] AD was issued, further investigations linked
to the WFD analysis highlighted that, to meet the WFD requirements,
it is necessary to require
[[Page 38093]]
embodiment of the terminating action modification.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2016-0187, which is superseded, and requires
modification of all affected cargo doors, which constitutes
terminating action for the repetitive SDI[s] required by this [EASA]
AD.
The related investigative action is a high frequency eddy current
(HFEC) rotating probe inspection for cracks. Corrective actions
include, among other things, oversizing and cold-expanding any affected
holes and repair. 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-2018-0641.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Service Bulletin A320-52-1171, Revision 02, dated April
10, 2017, which describes procedures for repetitive special detailed
inspections of all frame forks in the beam 4 area of any affected door,
and corrective actions.
Service Bulletin A320-52-1042, Revision 2, dated January
14, 1997, which describes procedures for modification of all affected
forward and aft cargo compartment doors.
Service Bulletin A320-52-1170, including Appendices 01 and
02, dated September 5, 2016, which describes procedures for modifying
all affected forward and aft cargo compartment doors, including
oversize and cold working of riveting for all frame forks.
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 these
same type designs.
Explanation of Compliance Time
The compliance time for the replacement specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is replaced before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to flight. We will not grant any extensions of the
compliance time to complete any AD-mandated service bulletin related to
WFD without extensive new data that would substantiate and clearly
warrant such an extension.
Paragraphs (j)(2) and (j)(3) of AD 2017-22-07 allowed an optional
terminating modification that could be done at any time. This proposed
AD would still permit that optional terminating modification, but with
new limitations on the compliance time, i.e., the optional modification
must be done on or after the accumulation of 21,700 flight cycles since
first installation of the door on an airplane in order to terminate the
repetitive inspections. The repetitive inspections are not terminated
if the modification is done before the accumulation of 21,700 flight
cycles since first installation of the door on an airplane. These
limitations match those in EASA AD 2018-0024, dated January 29, 2018.
Costs of Compliance
We estimate that this proposed AD affects 88 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Modification.................... 24 work-hours x Up to $240........ Up to $2,280...... Up to $200,640.
$85 per hour =
$2,040.
Inspection...................... 25 work-hours x $0................ $2,125............ $187,000.
$85 per hour =
$2,125.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator.
Subtitle VII: Aviation Programs, describes in more detail the scope
of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes 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.
[[Page 38094]]
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
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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]
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2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2017-22-07, Amendment 39-19087 (82 FR 56158, November 28, 2017), and
adding the following new AD:
Airbus: Docket No. FAA-2018-0641; Product Identifier 2018-NM-032-AD.
(a) Comments Due Date
We must receive comments by September 17, 2018.
(b) Affected ADs
This AD replaces AD 2017-22-07, Amendment 39-19087 (82 FR 56158,
November 28, 2017) (``AD 2017-22-07'').
(c) Applicability
This AD applies to Airbus Model A319-111, -112, -113, -114, -
115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -
216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131,
-211, -212, -213, -231, and -232 airplanes, certificated in any
category, manufacturer serial numbers through 0758 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 52, Doors.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the frame forks and outer skin on the
forward and aft cargo compartment doors are subject to widespread
fatigue damage (WFD), and a determination that a modification of the
frame forks must be accomplished. We are issuing this AD to address
cracks on the frame forks and outer skin on the forward and aft
cargo compartment doors, which could lead to reduced structural
integrity and failure of the cargo compartment door, possible
decompression of the airplane, and injury to occupants.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Definition of Affected Door, With No Changes
This paragraph restates the definition in paragraph (g) of AD
2017-22-07, with no changes. For the purpose of this AD, an
``affected door'' is a forward or aft cargo compartment door, having
any part number listed in table 1 to paragraph (g) of this AD,
except a cargo compartment door on which Airbus Service Bulletin
A320-52-1042 or Airbus Service Bulletin A320-52-1170 is embodied.
[GRAPHIC] [TIFF OMITTED] TP03AU18.000
(h) Retained Repetitive Special Detailed Inspection of Frame Forks,
With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2017-22-07, with no changes. At the latest of the compliance times
listed in paragraphs (h)(1) through (h)(4) of this AD: Do a special
detailed inspection of all frame forks in the beam 4 area of any
affected door as defined in paragraph (g) of this AD, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-52-1171, Revision 02, dated April 10, 2017, except as specified
in paragraphs (l) and (m) of this AD. Repeat the inspection
thereafter at intervals not to exceed 3,000 flight cycles. A review
of the airplane delivery or maintenance records is acceptable to
identify any affected door installed on the airplane, provided that
the cargo compartment door part number can be conclusively
determined from that review.
(1) Before exceeding 37,500 flight cycles since first
installation of the door on an airplane.
(2) Within 900 flight cycles after January 2, 2018 (the
effective date of AD 2017-22-07), without exceeding 41,950 flight
cycles since first installation of the door on an airplane.
(3) Within 50 flight cycles after January 2, 2018 (the effective
date of AD 2017-22-07), for a door having reached or exceeded 41,900
flight cycles since first installation on an airplane.
[[Page 38095]]
(4) Within 3,000 flight cycles since the last inspection of the
door as specified in Airbus Service Bulletin A320-52-1032.
(i) Retained Corrective Actions, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2017-22-07, with no changes. If any crack is found during any
inspection required by paragraph (h) of this AD, before further
flight, do all applicable corrective actions in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-52-1171,
Revision 02, dated April 10, 2017, except as specified in paragraphs
(l) and (m) of this AD. Accomplishment of applicable corrective
actions does not constitute terminating action for the repetitive
inspections.
(j) Terminating Modification
Before the accumulation of 56,300 total flight cycles, but not
before the accumulation of 21,700 total flight cycles since first
installation of the affected door on an airplane: Modify all
affected doors of an airplane, including accomplishment of all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1170, including Appendices 01 and 02, dated
September 5, 2016. Accomplishing this modification constitutes
terminating action for the repetitive inspections specified in
paragraph (h) of this AD for that airplane, provided that, after
modification, no affected door is re-installed on that airplane.
(k) Retained Optional Terminating Action, With Changes Related to
Compliance
This paragraph restates the requirements of paragraph (j) of AD
2017-22-07, with changes related to compliance.
(1) Modification of all affected doors of an airplane before the
effective date of this AD, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-52-1042, Revision 2,
dated January 14, 1997, constitutes terminating action for the
repetitive inspections specified in paragraph (h) of this AD and a
method of compliance for the modification required by paragraph (j)
of this AD, for that airplane, provided that, after modification, no
affected door is re-installed on that airplane. On or after the
effective date of this AD, the modification required by paragraph
(j) of this AD must be done.
(2) Modification of all affected doors of an airplane including
accomplishment of all applicable related investigative and
corrective actions, if done before the effective date of this AD in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1170, dated September 5, 2016, except as specified
in paragraph (l) of this AD, constitutes terminating action for the
repetitive inspections specified in paragraph (h) of this AD and a
method of compliance for the modification required by paragraph (j)
of this AD, for that airplane, provided that, after modification, no
affected door is re-installed on that airplane. On or after the
effective date of this AD, the modification required by paragraph
(j) of this AD must be done.
(3) Modification of all affected doors on an airplane, in case
of finding damaged frame forks, as specified in an Airbus Repair
Design Approval Sheet (RDAS), if done before the effective date of
this AD and done in accordance with 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); constitutes terminating action for the
repetitive inspection specified in paragraph (h) of this AD and a
method of compliance for the modification required by paragraph (j)
of this AD, for that airplane, provided that, after modification, no
affected door is re-installed on that airplane. On or after the
effective date of this AD, the modification required by paragraph
(j) of this AD must be done.
(l) Retained Exception to Service Information
This paragraph restates the requirements of paragraph (k) of AD
2017-22-07, with no changes. Where Airbus Service Bulletin A320-52-
1170, including Appendices 01 and 02, dated September 5, 2016; or
Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10,
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 (p)(2) of this AD.
(m) Retained No Reporting Requirement
This paragraph restates the requirements of paragraph (l) of AD
2017-22-07, with no changes. Although Airbus Service Bulletin A320-
52-1171, Revision 02, dated April 10, 2017, specifies to submit
certain information to the manufacturer, and specifies that action
as ``RC,'' this AD does not include that requirement.
(n) Retained Credit for Previous Actions
This paragraph restates the requirements of paragraph (m) of AD
2017-22-07, with no changes.
(1) This paragraph provides credit for the actions required by
paragraphs (h) and (i) of this AD, if those actions were performed
before January 2, 2018 (the effective date of AD 2017-22-07), using
Airbus Service Bulletin A320-52-1171, dated October 29, 2015,
provided that it can be conclusively determined that any part number
D52371000018 was also inspected as specified in paragraph (h) of
this AD.
(2) This paragraph provides credit for the actions required by
paragraphs (h) and (i) of this AD, if those actions were performed
before January 2, 2018 (the effective date of AD 2017-22-07), using
Airbus Service Bulletin A320-52-1171, Revision 01, dated September
5, 2016.
(o) Parts Installation Limitation
As of the effective date of this AD, no person may install, on
any airplane, an affected door specified in paragraph (g) of this
AD, unless less than 56,300 flight cycles have accumulated since
first installation of the door on an airplane, and unless the door
has been inspected in accordance with the requirements of paragraph
(h) of this AD and all applicable corrective actions have been done
in accordance with paragraph (i) of this AD.
(p) 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 (p)(2) of this AD. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus's EASA Design Organization Approval
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): Except as specified in
paragraphs (l) and (m) 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.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2018-0024, dated January 29,
2018, for related information. This MCAI may be found in the AD
docket on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2018-0641.
(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, 2 Rond Point Emile Dewoitine,
31700 Blagnac Cedex, France; telephone: +33
[[Page 38096]]
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 July 24, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-16497 Filed 8-2-18; 8:45 am]
BILLING CODE 4910-13-P
