Airworthiness Directives; Airbus SAS Airplanes, 52126-52131 [2018-22147]
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52126
Federal Register / Vol. 83, No. 200 / Tuesday, October 16, 2018 / Rules and Regulations
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3220.
[Docket No. FAA–2018–0583; Product
Identifier 2018–NM–019–AD; Amendment
39–19453; AD 2018–20–19]
series airplanes; and Model A340–313
airplanes. AD 2017–16–07 required
inspection of the fuselage bulk cargo
door frames at specific locations, and
corrective action if necessary. This AD
requires new inspections of certain
attachment holes for residual surface
treatment and cracking, and corrective
action if necessary; and provides an
optional terminating action for the
inspections. This AD also revises the
applicability to add certain airplanes
and remove others. This AD was
prompted by a determination that only
airplanes having certain manufacturer
serial numbers (MSNs) are affected by
tartaric sulfuric anodizing (TSA)/
chromic acid anodizing (CAA) surface
treatment in the door fitting attachment
holes, and that airplanes having certain
MSNs were excluded. This AD is
intended to complete certain mandated
programs intended to support the
airplane reaching its limit of validity
(LOV) of the engineering data that
support the established structural
maintenance program. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective November
20, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 20, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAL, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France, France;
telephone +33 5 61 93 36 96; fax +33 5
61 93 45 80; email airworthiness.A330A340@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.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0583.
RIN 2120–AA64
Examining the AD Docket
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) ATR ATR42–400/–500, Time Limits
Document (TL), Revision 11, dated May 5,
2015.
(ii) ATR ATR42–400/–500 Time Limits
Temporary Revision TR01/17, dated May 3,
2017.
(3) For service information identified in
this AD, contact ATR GIE Avions de
Transport Re´gional, 1, Alle´e Pierre Nadot,
31712 Blagnac Cedex, France; telephone +33
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
email continued.airworthiness@atr
aircraft.com; internet https://www.atraircraft.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
September 25, 2018.
John P. Piccola,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–22140 Filed 10–15–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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AGENCY:
We are superseding
Airworthiness Directive (AD) 2017–16–
07, which applied to certain Airbus SAS
Model A330–200, A330–200 Freighter,
A330–300, A340–500, and A340–600
SUMMARY:
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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–
0583; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
U.S. Department of Transportation,
PO 00000
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Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION 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.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2017–16–07,
Amendment 39–18984 (82 FR 41874,
September 5, 2017) (‘‘AD 2017–16–07’’).
AD 2017–16–07 applied certain Airbus
Model A330–200, A330–200 Freighter,
A330–300, A340–500, and A340–600
series airplanes; and Model A340–313
airplanes. The NPRM published in the
Federal Register on July 6, 2018 (83 FR
31499). The NPRM was prompted by a
determination that only airplanes
having certain MSNs are affected by
TSA/CAA surface treatment in the door
fitting attachment holes, and that
airplanes having certain MSNs were
excluded. The NPRM was intended to
complete certain mandated programs
intended to support the airplane
reaching its LOV of the engineering data
that support the established structural
maintenance program. The NPRM
proposed to require new inspections of
certain attachment holes for residual
surface treatment and cracking, and
corrective action if necessary; and to
provide an optional terminating action
for the inspections. The NPRM also
proposed to revise the applicability to
add certain airplanes and remove
others. We are issuing this AD to
address fatigue cracks in the bulk cargo
door frames, caused by TSA/CAA
surface treatment in certain bulk cargo
door frame holes. Cracks in the bulk
cargo door frames can cause the in-flight
loss of a bulk cargo door, damage to the
airplane, and subsequent reduced
control of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0005,
dated January 10, 2018 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus SAS Model A330–
200, A330–200 Freighter, and A330–300
series airplanes, and Airbus SAS Model
A340–200 and A340–300 series
airplanes. The MCAI states:
In the frame of the certification of the A330
Extended Service Goal exercise, it was
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Federal Register / Vol. 83, No. 200 / Tuesday, October 16, 2018 / Rules and Regulations
identified that Tartaric Sulfuric Anodising
(TSA) or Chromic Acid Anodising (CAA)
surface treatment is present in some frame
holes, from aeroplane MSN [manufacturer
serial number] 0400 and later MSN,
following production process modification.
On bulk cargo door frames (FR) 67 and FR
69 right hand (RH) side, the door fitting
attachment holes have this TSA or CAA
treatment, which leads to a detrimental effect
on fatigue behaviour.
This condition, if not detected and
corrected, could lead to cracks in the primary
structure, possibly resulting in in-flight loss
of a bulk cargo door, consequent
decompression and potential damage to, and
reduced control of, the aeroplane.
To initially address this potential unsafe
condition, Airbus issued Alert Operators
Transmission (AOT) A53L012–16 to provide
instructions to inspect the fuselage bulk
cargo door frames at specific locations.
Consequently, EASA issued AD 2016–0102
[which corresponds to FAA AD 2017–16–07],
requiring repetitive non-destructive test
(rototest and high-frequency eddy-current
(HFEC)) inspection or visual detailed (DET)
inspections [to detect cracking] of the
affected areas, and, depending on findings,
accomplishment of a repair.
Since that [EASA] AD was issued, it was
determined that only aeroplanes from MSN
0400 to MSN 1779 are affected by CAA or
TSA surface treatment issue in the door
fitting attachment holes. However, it was also
determined that aeroplanes MSN 0001 to
MSN 0399 are affected in the same
attachment holes due to a fatigue issue,
therefore, the same inspections must also be
accomplished on these aeroplanes. In
addition, based on inspection results and
calculation, Airbus redefined inspection
thresholds and intervals, depending on
aeroplane type, model and utilisation. Airbus
published SB A330–53–3278 and SB A340–
53–4239 providing the inspection
instructions at the specific locations with
extended inspection thresholds and intervals.
Airbus also determined that the actions
should not be required for A340–500 and
–600 models, as for these aeroplanes, the
unsafe condition would only develop beyond
the Design Service Goal of these aeroplanes.
Finally, Airbus developed modification
(mod) 206409 and published associated SB
A330–53–3275 and SB A340–53–4238, as
applicable, as optional terminating action.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2016–0102, which is superseded,
expands the Applicability and requires
redefined repetitive inspections of the holes
at the upper and lower door support fittings
of FR 67 and FR 69 RH and the holes at door
latch fitting of FR 69 RH. This [EASA] AD
also introduces an optional modification,
which constitutes terminating action for the
repetitive inspections as required by this
[EASA] AD.
The optional modification involves
related investigative actions of eddy
current rotating probe testing for cracks
of the support fittings and the frame
holes at frame (FR) 67 and FR 69. 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–
0583.
Comments
We gave the public the opportunity to
participate in developing this final rule.
We received no comments on the NPRM
or on the determination of the cost to
the public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes. We have determined
that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
52127
Related Service Information Under 1
CFR Part 51
Airbus SAS has issued the following
service information.
• Service Bulletin A330–53–3275,
dated September 8, 2017.
• Service Bulletin A330–53–3278,
dated August 22, 2017.
• Service Bulletin A340–53–4238,
dated September 8, 2017.
• Service Bulletin A340–53–4239,
dated September 5, 2017.
Airbus Service Bulletins A330–53–
3278 and A340–53–4239 describe
procedures for rototest, HFEC/ultrasonic
and detailed inspections for residual
surface treatment and cracking of the
upper and lower right-hand fuselage
bulk cargo door support fitting
attachment holes at FR 67 and FR 69
and the right-hand fuselage bulk cargo
door latch fitting attachment holes at FR
69. Airbus Service Bulletins A330–53–
3275 and A340–53–4238 describe
procedures for a modification, which
includes eddy current rotating probe
testing for cracks of the support fittings
and the frame holes at FR 67 and FR 69,
and removal of TSA or CAA in the final
holes of the bulk door frames FR 67 and
FR 69. These documents are distinct
since they apply to different airplane
models. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 102
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Inspections and modification ..............
Up to 40 work-hours × $85 per hour
= $3,400.
We have received no definitive data
that enables us to provide cost estimates
for the on-condition actions specified in
this AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
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Parts cost
$5,100
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
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Cost per product
Up to $8,500 ........
Cost on U.S. operators
Up to $867,000.
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
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delegated the authority to issue ADs
applicable to transport category
airplanes and associated appliances to
the Director of the System Oversight
Division.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
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■
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2017–16–07, Amendment 39–18984 (82
FR 41874, September 5, 2017), and
adding the following new AD:
■
2018–20–19 Airbus SAS: Amendment 39–
19453; Docket No. FAA–2018–0583;
Product Identifier 2018–NM–019–AD.
(a) Effective Date
This AD is effective November 20, 2018.
(b) Affected ADs
This AD replaces AD 2017–16–07,
Amendment 39–18984 (82 FR 41874,
September 5, 2017) (‘‘AD 2017–16–07’’).
(c) Applicability
This AD applies to the following Airbus
SAS airplanes, certificated in any category,
manufacturer serial numbers (MSNs) 0001 to
1779 inclusive; except airplanes on which
Airbus Service Bulletin A330–53–3275 or
Airbus Service Bulletin A340–53–4238 has
been embodied.
(1) Model A330–201, –202, –203, –223, and
–243 airplanes.
(2) Model A330–223F and –243F airplanes.
(3) Model A330–301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes.
(4) Model A340–211, –212, and –213
airplanes.
(5) Model A340–311, –312, and –313
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD is prompted by a determination
that only airplanes having certain MSNs are
affected by tartaric sulfuric anodizing (TSA)/
chromic acid anodizing (CAA) surface
treatment in the door fitting attachment
holes, and that airplanes having certain
MSNs were excluded from AD 2017–16–07.
This AD is intended to complete certain
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mandated programs intended to support the
airplane reaching its limit of validity (LOV)
of the engineering data that support the
established structural maintenance program.
We are issuing this AD to detect and correct
fatigue cracks in the bulk cargo door frames,
caused by TSA/CAA surface treatment in
certain bulk cargo door frame holes. Cracks
in the bulk cargo door frames can cause the
in-flight loss of a bulk cargo door, damage to
the airplane, and subsequent reduced control
of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
Before exceeding the thresholds specified
in table 1 to paragraph (g) of this AD, or
within the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD,
whichever is later: Do a rototest, high
frequency eddy current (HFEC), ultrasonic, or
detailed inspection, as applicable, for
residual surface treatment and cracking of the
upper and lower right-hand fuselage bulk
cargo door support fitting attachment holes at
FR 67 and FR 69 and the right-hand fuselage
bulk cargo door latch fitting attachment holes
at FR 69, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3278, dated
August 22, 2017; or Airbus Service Bulletin
A340–53–4239, dated September 5, 2017; as
applicable. Thereafter, depending on the
areas and inspection methods as defined in
table 2 to paragraph (g) of this AD, repeat the
inspection at intervals not exceeding those
specified in table 3 to paragraph (g) of this
AD.
(1) For airplanes having MSN 0001 through
0399 inclusive: Within 200 flight cycles after
the effective date of this AD.
(2) For airplanes having MSN 0400 through
1779 inclusive: Within 800 flight cycles after
the effective date of this AD.
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Table 1 to paragraph (g) of this AD -Initial Inspection
Affected
Airplanes
MSN
A330
(except -200F),
A340-200, and
A340-300
0001 to
0399
inclusive
A330
(except -200F),
A340-200, and
A340-300
0400 to
1779
inclusive
A330-223F
and -243F
All
Operation: Short- Inspection Threshold (flight
range (SR);
cycles [FC] or flight hours
Long-range
[FH], whichever occurs first,
(LR)*
since airplane first flight)
SR
27,100 FC or 83,900 FH
LR
23,600 FC or 133,100 FH
SR
16,000 FC or 49,500 FH
LR
13,900 FC or 78,600 FH
SRorLR
11,300 FC or 34,000 FH
*Guidance for determining whether an airplane is operated in short-range or longrange operations can be found in Airbus Operator Information Telex 999.0086111.
Table 2 to paragraph (g) of this AD -Areas and Inspection Methods
Action
Areas to be Inspected
Inspection Methods*
1
Any
Detailed
Upper and lower door support fitting holes
Rototest
Latch fitting holes
HFEC
Upper door support fitting hole
HFEC and ultrasonic
2
3
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*The inspection interval, as specified in table 3 to paragraph (g) ofthis AD, is based
on the kind of inspection (action) applied to an area, along with the airplane model.
Alternating between inspection methods is allowed, provided that the applicable
inspection interval is based on the method used during the latest inspection.
Federal Register / Vol. 83, No. 200 / Tuesday, October 16, 2018 / Rules and Regulations
BILLING CODE 4910–13–C
(h) Corrective Action
If any discrepancy is found during any
inspection required by paragraph (g) of this
AD, before further flight, repair using a
method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus SAS’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
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(i) Non-Terminating Action for Repairs
Accomplishment of a repair on an airplane,
as required by paragraph (h) of this AD, does
not constitute terminating action for the
inspections required by paragraph (g) of this
AD for that airplane, unless otherwise
specified in repair instructions approved by
the Manager, International Section, Transport
Standards Branch, FAA; or EASA; or Airbus
SAS’s EASA DOA. If approved by the DOA,
the approval must include the DOAauthorized signature.
(j) Optional Terminating Action
Accomplishment of the modification,
including applicable related investigative
and corrective actions and removal of TSA or
CAA in the final holes of the bulk door
frames FR 67 and FR 69, as applicable,
specified in, and in accordance with the AI
of Airbus Service Bulletin A330–53–3275,
dated September 8, 2017; or Airbus Service
Bulletin A340–53–4238, dated September 8,
2017; as applicable; constitutes terminating
action for the inspections required by
paragraph (g) of this AD for that airplane,
unless otherwise specified in the repair
instructions approved by the Manager,
International Section, Transport Standards
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Branch, FAA; or EASA; or Airbus SAS’s
EASA DOA. If approved by the DOA, the
approval must include the DOA-authorized
signature.
(k) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Alert
Operators Transmission (AOT) A53L012–16,
dated May 30, 2016; or Rev 01, dated March
9, 2017.
(l) 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 manager of the International
Section, send it to the attention of the person
identified in paragraph (m)(2) of this AD.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: 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 SAS’s EASA DOA. If approved by the
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DOA, the approval must include the DOAauthorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0005, dated January 10, 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–2018–0583.
(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) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330–53–3275,
dated September 8, 2017.
(ii) Airbus Service Bulletin A330–53–3278,
dated August 22, 2017.
(iii) Airbus Service Bulletin A340–53–
4238, dated September 8, 2017.
(iv) Airbus Service Bulletin A340–53–
4239, dated September 5, 2017.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France, France;
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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.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
September 26, 2018.
John P. Piccola,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–22147 Filed 10–15–18; 8:45 am]
Examining the AD Docket
BILLING CODE 4910–13–P
You may examine the AD docket on
the internet at https://
www.regulations.govby searching for
and locating Docket No. FAA–2017–
0771; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Joe
Salameh, Aerospace Engineer, Systems
and Equipment Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3536; email: joe.salameh@faa.gov.
SUPPLEMENTARY INFORMATION:
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0771; Product
Identifier 2016–NM–212–AD; Amendment
39–19449; AD 2018–20–15]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2015–09–
07, which applied to all The Boeing
Company Model 787 airplanes. AD
2015–09–07 required a repetitive
maintenance task for electrical power
deactivation. This AD requires installing
new software for the generator control
unit (GCU). This AD also removes
certain airplanes from the applicability.
This AD was prompted by the
determination that a Model 787 airplane
that has been powered continuously for
248 days can lose all alternating current
(AC) electrical power due to the GCUs
simultaneously going into failsafe mode.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective November
20, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 20, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
SUMMARY:
amozie on DSK3GDR082PROD with RULES
this AD as of May 1, 2015 (80 FR 24789,
May 1, 2015).
ADDRESSES: For service information
identified in this final rule, 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 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–2017–
0771.
VerDate Sep<11>2014
16:24 Oct 15, 2018
Jkt 247001
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2015–09–07,
Amendment 39–18153 (80 FR 24789,
May 1, 2015) (‘‘AD 2015–09–07’’). AD
2015–09–07 applied to all The Boeing
Company Model 787 airplanes. The
NPRM published in the Federal
Register on August 15, 2017 (82 FR
38629). The NPRM was prompted by the
determination that a Model 787 airplane
that has been powered continuously for
248 days can lose all AC electrical
power due to the GCUs simultaneously
going into failsafe mode. This condition
is caused by a software counter internal
to the GCUs that will overflow after 248
days of continuous power. The NPRM
proposed to require installing the new
GCU software developed to address the
software counter overflow anomaly. The
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
52131
NPRM also proposed to remove certain
airplanes from the applicability. We are
issuing this AD to address loss of all AC
electrical power, which could result in
loss of control of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Support for the NPRM
The Air Line Pilots Association,
International (ALPA) and American
Airlines indicated their support for the
NPRM.
Request To Update Number of Affected
Airplanes
Boeing requested that we update the
Costs of Compliance section of the
proposed AD to state that ‘‘55 airplanes
of U.S. registry’’ are affected. Boeing
noted that its records show 55 Nregistered airplanes, not 47 as stated in
the proposed AD.
We agree with the commenter’s
request for the reason provided. We
have updated the Costs of Compliance
section of this AD accordingly.
Request To Revise Warranty
Information in Costs of Compliance
Section
Boeing requested that we revise the
Costs of Compliance section of the
proposed AD to state that warranty
remedies are not available for Boeing
Service Bulletin B787–81205–
SB240063–00, Issue 002, dated June 7,
2016. Boeing noted that Boeing Service
Bulletin B787–81205–SB240063–00,
Issue 002, dated June 7, 2016, states
‘‘Boeing warranty remedies are not
available for the configuration changes
set forth in this service bulletin.
Notwithstanding, Boeing will provide
the supplier software referenced in this
service bulletin at no charge. This offer
will expire eight years from the original
issue date of this service bulletin.’’
We acknowledge the commenter’s
request and agree to clarify. The
warranty information in the Costs of
Compliance section of this AD is meant
to be informational, and is included
when the manufacturer’s service
information states warranty coverage
may be available. We do not control
warranty coverage and operators must
work with the manufacturer to
determine if they are eligible for a
warranty. We have revised the warranty
information in the Costs of Compliance
section of this AD to note that some of
the software costs may be covered under
warranty.
E:\FR\FM\16OCR1.SGM
16OCR1
]]>Agencies
[Federal Register Volume 83, Number 200 (Tuesday, October 16, 2018)]
[Rules and Regulations]
[Pages 52126-52131]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-22147]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0583; Product Identifier 2018-NM-019-AD; Amendment
39-19453; AD 2018-20-19]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2017-16-07,
which applied to certain Airbus SAS Model A330-200, A330-200 Freighter,
A330-300, A340-500, and A340-600 series airplanes; and Model A340-313
airplanes. AD 2017-16-07 required inspection of the fuselage bulk cargo
door frames at specific locations, and corrective action if necessary.
This AD requires new inspections of certain attachment holes for
residual surface treatment and cracking, and corrective action if
necessary; and provides an optional terminating action for the
inspections. This AD also revises the applicability to add certain
airplanes and remove others. This AD was prompted by a determination
that only airplanes having certain manufacturer serial numbers (MSNs)
are affected by tartaric sulfuric anodizing (TSA)/chromic acid
anodizing (CAA) surface treatment in the door fitting attachment holes,
and that airplanes having certain MSNs were excluded. This AD is
intended to complete certain mandated programs intended to support the
airplane reaching its limit of validity (LOV) of the engineering data
that support the established structural maintenance program. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective November 20, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 20,
2018.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile
Dewoitine No: 2, 31700 Blagnac Cedex, France, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 45 80; 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. It is also
available on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2018-0583.
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-
0583; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3229.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2017-16-07, Amendment 39-18984 (82 FR 41874,
September 5, 2017) (``AD 2017-16-07''). AD 2017-16-07 applied certain
Airbus Model A330-200, A330-200 Freighter, A330-300, A340-500, and
A340-600 series airplanes; and Model A340-313 airplanes. The NPRM
published in the Federal Register on July 6, 2018 (83 FR 31499). The
NPRM was prompted by a determination that only airplanes having certain
MSNs are affected by TSA/CAA surface treatment in the door fitting
attachment holes, and that airplanes having certain MSNs were excluded.
The NPRM was intended to complete certain mandated programs intended to
support the airplane reaching its LOV of the engineering data that
support the established structural maintenance program. The NPRM
proposed to require new inspections of certain attachment holes for
residual surface treatment and cracking, and corrective action if
necessary; and to provide an optional terminating action for the
inspections. The NPRM also proposed to revise the applicability to add
certain airplanes and remove others. We are issuing this AD to address
fatigue cracks in the bulk cargo door frames, caused by TSA/CAA surface
treatment in certain bulk cargo door frame holes. Cracks in the bulk
cargo door frames can cause the in-flight loss of a bulk cargo door,
damage to the airplane, and subsequent reduced control of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0005, dated January 10, 2018 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus SAS Model A330-200,
A330-200 Freighter, and A330-300 series airplanes, and Airbus SAS Model
A340-200 and A340-300 series airplanes. The MCAI states:
In the frame of the certification of the A330 Extended Service
Goal exercise, it was
[[Page 52127]]
identified that Tartaric Sulfuric Anodising (TSA) or Chromic Acid
Anodising (CAA) surface treatment is present in some frame holes,
from aeroplane MSN [manufacturer serial number] 0400 and later MSN,
following production process modification. On bulk cargo door frames
(FR) 67 and FR 69 right hand (RH) side, the door fitting attachment
holes have this TSA or CAA treatment, which leads to a detrimental
effect on fatigue behaviour.
This condition, if not detected and corrected, could lead to
cracks in the primary structure, possibly resulting in in-flight
loss of a bulk cargo door, consequent decompression and potential
damage to, and reduced control of, the aeroplane.
To initially address this potential unsafe condition, Airbus
issued Alert Operators Transmission (AOT) A53L012-16 to provide
instructions to inspect the fuselage bulk cargo door frames at
specific locations. Consequently, EASA issued AD 2016-0102 [which
corresponds to FAA AD 2017-16-07], requiring repetitive non-
destructive test (rototest and high-frequency eddy-current (HFEC))
inspection or visual detailed (DET) inspections [to detect cracking]
of the affected areas, and, depending on findings, accomplishment of
a repair.
Since that [EASA] AD was issued, it was determined that only
aeroplanes from MSN 0400 to MSN 1779 are affected by CAA or TSA
surface treatment issue in the door fitting attachment holes.
However, it was also determined that aeroplanes MSN 0001 to MSN 0399
are affected in the same attachment holes due to a fatigue issue,
therefore, the same inspections must also be accomplished on these
aeroplanes. In addition, based on inspection results and
calculation, Airbus redefined inspection thresholds and intervals,
depending on aeroplane type, model and utilisation. Airbus published
SB A330-53-3278 and SB A340-53-4239 providing the inspection
instructions at the specific locations with extended inspection
thresholds and intervals. Airbus also determined that the actions
should not be required for A340-500 and -600 models, as for these
aeroplanes, the unsafe condition would only develop beyond the
Design Service Goal of these aeroplanes. Finally, Airbus developed
modification (mod) 206409 and published associated SB A330-53-3275
and SB A340-53-4238, as applicable, as optional terminating action.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2016-0102, which is superseded, expands the
Applicability and requires redefined repetitive inspections of the
holes at the upper and lower door support fittings of FR 67 and FR
69 RH and the holes at door latch fitting of FR 69 RH. This [EASA]
AD also introduces an optional modification, which constitutes
terminating action for the repetitive inspections as required by
this [EASA] AD.
The optional modification involves related investigative actions of
eddy current rotating probe testing for cracks of the support fittings
and the frame holes at frame (FR) 67 and FR 69. 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-2018-0583.
Comments
We gave the public the opportunity to participate in developing
this final rule. We received no comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this final rule as proposed,
except for minor editorial changes. We have determined that these minor
changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Airbus SAS has issued the following service information.
Service Bulletin A330-53-3275, dated September 8, 2017.
Service Bulletin A330-53-3278, dated August 22, 2017.
Service Bulletin A340-53-4238, dated September 8, 2017.
Service Bulletin A340-53-4239, dated September 5, 2017.
Airbus Service Bulletins A330-53-3278 and A340-53-4239 describe
procedures for rototest, HFEC/ultrasonic and detailed inspections for
residual surface treatment and cracking of the upper and lower right-
hand fuselage bulk cargo door support fitting attachment holes at FR 67
and FR 69 and the right-hand fuselage bulk cargo door latch fitting
attachment holes at FR 69. Airbus Service Bulletins A330-53-3275 and
A340-53-4238 describe procedures for a modification, which includes
eddy current rotating probe testing for cracks of the support fittings
and the frame holes at FR 67 and FR 69, and removal of TSA or CAA in
the final holes of the bulk door frames FR 67 and FR 69. These
documents are distinct since they apply to different airplane models.
This service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 102 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections and modification Up to 40 $5,100 Up to $8,500... Up to $867,000.
work[dash]hour
s x $85 per
hour = $3,400.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that enables us to provide cost
estimates for the on-condition actions specified in this AD.
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
[[Page 52128]]
delegated the authority to issue ADs applicable to transport category
airplanes and associated appliances to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2017-16-07, Amendment 39-18984 (82 FR 41874, September 5, 2017), and
adding the following new AD:
2018-20-19 Airbus SAS: Amendment 39-19453; Docket No. FAA-2018-0583;
Product Identifier 2018-NM-019-AD.
(a) Effective Date
This AD is effective November 20, 2018.
(b) Affected ADs
This AD replaces AD 2017-16-07, Amendment 39-18984 (82 FR 41874,
September 5, 2017) (``AD 2017-16-07'').
(c) Applicability
This AD applies to the following Airbus SAS airplanes,
certificated in any category, manufacturer serial numbers (MSNs)
0001 to 1779 inclusive; except airplanes on which Airbus Service
Bulletin A330-53-3275 or Airbus Service Bulletin A340-53-4238 has
been embodied.
(1) Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Model A330-223F and -243F airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes.
(4) Model A340-211, -212, and -213 airplanes.
(5) Model A340-311, -312, and -313 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD is prompted by a determination that only airplanes
having certain MSNs are affected by tartaric sulfuric anodizing
(TSA)/chromic acid anodizing (CAA) surface treatment in the door
fitting attachment holes, and that airplanes having certain MSNs
were excluded from AD 2017-16-07. This AD is intended to complete
certain mandated programs intended to support the airplane reaching
its limit of validity (LOV) of the engineering data that support the
established structural maintenance program. We are issuing this AD
to detect and correct fatigue cracks in the bulk cargo door frames,
caused by TSA/CAA surface treatment in certain bulk cargo door frame
holes. Cracks in the bulk cargo door frames can cause the in-flight
loss of a bulk cargo door, damage to the airplane, and subsequent
reduced control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Before exceeding the thresholds specified in table 1 to
paragraph (g) of this AD, or within the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD, whichever is later: Do a
rototest, high frequency eddy current (HFEC), ultrasonic, or
detailed inspection, as applicable, for residual surface treatment
and cracking of the upper and lower right-hand fuselage bulk cargo
door support fitting attachment holes at FR 67 and FR 69 and the
right-hand fuselage bulk cargo door latch fitting attachment holes
at FR 69, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A330-53-3278, dated August 22, 2017; or
Airbus Service Bulletin A340-53-4239, dated September 5, 2017; as
applicable. Thereafter, depending on the areas and inspection
methods as defined in table 2 to paragraph (g) of this AD, repeat
the inspection at intervals not exceeding those specified in table 3
to paragraph (g) of this AD.
(1) For airplanes having MSN 0001 through 0399 inclusive: Within
200 flight cycles after the effective date of this AD.
(2) For airplanes having MSN 0400 through 1779 inclusive: Within
800 flight cycles after the effective date of this AD.
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(h) Corrective Action
If any discrepancy is found during any inspection required by
paragraph (g) of this AD, before further flight, repair using a
method approved by the Manager, International Section, Transport
Standards Branch, FAA; or the European Aviation Safety Agency
(EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
(i) Non-Terminating Action for Repairs
Accomplishment of a repair on an airplane, as required by
paragraph (h) of this AD, does not constitute terminating action for
the inspections required by paragraph (g) of this AD for that
airplane, unless otherwise specified in repair instructions approved
by the Manager, International Section, Transport Standards Branch,
FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the
approval must include the DOA-authorized signature.
(j) Optional Terminating Action
Accomplishment of the modification, including applicable related
investigative and corrective actions and removal of TSA or CAA in
the final holes of the bulk door frames FR 67 and FR 69, as
applicable, specified in, and in accordance with the AI of Airbus
Service Bulletin A330-53-3275, dated September 8, 2017; or Airbus
Service Bulletin A340-53-4238, dated September 8, 2017; as
applicable; constitutes terminating action for the inspections
required by paragraph (g) of this AD for that airplane, unless
otherwise specified in the repair instructions approved by the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(k) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Airbus Alert Operators Transmission
(AOT) A53L012-16, dated May 30, 2016; or Rev 01, dated March 9,
2017.
(l) 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 manager of the International Section, send it to the
attention of the person identified in paragraph (m)(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: 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 SAS's EASA DOA. If approved by
the DOA, the approval must include the DOA-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2018-0005, dated January 10, 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-2018-0583.
(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) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330-53-3275, dated September 8,
2017.
(ii) Airbus Service Bulletin A330-53-3278, dated August 22,
2017.
(iii) Airbus Service Bulletin A340-53-4238, dated September 8,
2017.
(iv) Airbus Service Bulletin A340-53-4239, dated September 5,
2017.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France, France;
[[Page 52131]]
telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email
[email protected]; internet https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on September 26, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-22147 Filed 10-15-18; 8:45 am]
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