Airworthiness Directives; Airbus Airplanes, 56859-56865 [2017-25557]
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56859
Rules and Regulations
Federal Register
Vol. 82, No. 230
Friday, December 1, 2017
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0476; Product
Identifier 2016–NM–110–AD; Amendment
39–19111; AD 2017–24–07]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
jstallworth on DSKBBY8HB2PROD with RULES
Examining the AD Docket
We are superseding
Airworthiness Directive (AD) 2014–08–
01, which applied to all Airbus Model
A318, A319, A320, and A321 series
airplanes. AD 2014–08–01 required an
inspection for part numbers of the
interconnecting struts and, for affected
interconnecting struts, identification of
the part and serial numbers of the
associated target and proximity sensors
and replacement or re-identification of
the flap interconnecting strut if
necessary. This AD continues to require
an inspection to verify the
interconnecting strut part number. This
AD also provides a new compliance
time and an additional inspection for
previously inspected airplanes. This AD
was prompted by an investigation that
showed that when a certain
combination of target/proximity sensor
serial numbers is installed on a flap
interconnecting strut, a ‘‘target FAR’’
signal cannot be detected when reaching
the mechanical end stop of the
interconnecting strut. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective January 5,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 5, 2018.
SUMMARY:
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The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of March 26, 2014 (79 FR
9398, February 19, 2014).
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office—EIAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Standards Branch, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0476.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0476; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, Washington
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2014–08–01,
Amendment 39–17825 (79 FR 23900,
April 29, 2014) (‘‘AD 2014–08–01’’). AD
2014–08–01 applied to all Airbus Model
A318, A319, A320, and A321 series
airplanes. The NPRM published in the
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Federal Register on May 19, 2017 (82
FR 22918).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0113,
dated June 15, 2016 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A318, A319, A320,
and A321 series airplanes. The MCAI
states:
The flap interconnecting strut is a safety
device of the High Lift System which acts as
an alternative load path from one flap surface
to another in case of a flap drive system
disconnection. In such a failure case, the
installed proximity sensors provide
information to the slat flap control computer
(SFCC) and the operation of the flap drive
system is inhibited.
An engineering investigation showed that,
when a certain combination of target/sensor
serial number (s/n) is installed on a flap
interconnecting strut, a ‘‘target FAR’’ signal
cannot be detected when reaching the
mechanical end stop of the interconnecting
strut.
This condition, if not corrected, could
cause a flap down drive disconnection to
remain undetected, due to an already-failed
interconnecting strut sensor, potentially
resulting in asymmetric flap panel movement
and consequent loss of control of the
aeroplane.
To address this potential unsafe condition,
Airbus issued Service Bulletin (SB) A320–
27–1206 and SB A320–57–1164, to provide
identification and replacement instructions
for struts that have a certain target/sensor s/
n combination installed. Aeroplanes on
which modification (mod) 27956 had been
accomplished in production were identified
as not affected by the unsafe condition.
Consequently, EASA issued [EASA] AD
2012–0012 [which corresponds to FAA AD
2014–08–01] to require accomplishment of
these inspections and corrective actions.
Since that [EASA] AD was issued, Airbus
has informed EASA about a batch of
aeroplanes that were delivered with pre-mod
27956 Part Number (P/N) flap
interconnecting strut(s) installed, but
declared to be in post-mod configuration in
the Aircraft Inspection Report. Airbus SB
A320–57–1202 has been issued to provide
instructions to verify the interconnecting
strut P/N, and to update aircraft
documentation.
In addition, to ensure that all pre-mod
parts are checked and corrected as required,
SB A320–27–1206 was revised to include a
wider range of P/N of affected
interconnecting struts.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
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AD 2012–0012, which is superseded,
expands the Applicability [adds affected part
numbers], changes the compliance time and
requires an additional inspection for
aeroplanes that have already been inspected.
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–2017–
0476.
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. United
Airlines and the Air Line Pilots
Association, International supported the
NPRM.
Request To Add Additional
Identification Steps
Delta Airlines (DAL) requested that
additional identification steps be
required in the NPRM to ensure that the
affected parts are correctly identified.
DAL stated that figure 1 to paragraphs
(g) and (h) of the proposed AD contains
part numbers for affected
interconnecting struts. DAL commented
that a review of its records from
inspections conducted during
compliance with AD 2014–08–01
determined that other part numbers
were possible. DAL stated that it has
had at least one instance of a part with
the part number D5757032200000A.
DAL stated that figure 2 to paragraphs
(i)(2), (k), and (l) of the proposed AD
adds the provision that additional
alphanumeric characters may exist. DAL
commented that while the NPRM
removes some of the ambiguity that
existed in AD 2014–08–01, a review of
Airbus’s Aircraft Illustrated Parts
Catalog (AIPC) does not show any parts
with a ‘‘letter’’ suffix. DAL provided a
photo that showed that the part number
appears to ‘‘wrap’’ (to the next line) on
the part. DAL stated that this
‘‘wrapping’’ condition has led to
confusion in identifying the parts.
DAL stated that per the Airbus AIPC
Front Matter, the 13th, 14th, and 15th
characters are controlled in specific
ways. DAL also stated that the 13th and
14th characters are expected to be ‘‘00’’
and are used to fill out 12-digit base
numbers on the part installed during
production. DAL stated that the 15th
character is a paint code designator and
found the use of a paint code designator
unusual on a part that is not viewable
or expected to be painted to match an
air carrier paint scheme. DAL
commented that it believes the AD
should be updated to show 00A, 00B, or
the list of true possibilities, and the
XXX allowance creates a significant
number of possible part numbers that
DAL must identify as prohibited.
We agree to clarify the requirement to
identify affected parts. Regarding the
characters in the part number,
identifying the last three characters are
not required to identify a discrepant
part; only the first twelve base numbers
are required. Therefore, we do not agree
to revise this AD to include a complete
list of all possible combinations of these
characters.
We acknowledge the commenter’s
concern about the ‘‘wrapping’’
condition for part identification.
However, in the photo provided by the
commenter only the last three characters
are ‘‘wrapped.’’ As stated previously,
the last three characters are not required
to identify a discrepant part.
Formatting Change to a Figure
Figure 3 to paragraph (k)(1) of this AD
has been reformatted to clarify affected
manufacturer serial numbers.
Records Review
We have determined that a review of
maintenance records is acceptable for
complying with the actions specified in
paragraphs (i)(1) and (i)(2) of this AD,
provided the part number of the
installed interconnecting struts and the
part number and the serial number of
the associated target and proximity
sensor can be conclusively determined
from that review. We have revised
paragraph (i) of this AD accordingly.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–27–1206, Revision 02, dated
November 2, 2015. The service
information describes procedures for an
inspection to determine the part number
of the installed interconnecting struts
and the part number and serial number
of the associated target and proximity
sensors, and procedures for replacement
and re-identification of the
interconnecting struts. 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 1,032
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Cost per
product
Inspection and replacement (retained actions
from AD 2014–08–01).
Inspection and replacement (new action) .......
jstallworth on DSKBBY8HB2PROD with RULES
Labor cost
8 work-hours × $85 per hour = $680 .............
$0
$680
$701,760
15 work-hours × $85 per hour = $1,275 ........
0
1,275
1,315,800
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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Parts cost
Cost on U.S.
operators
Action
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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detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
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promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this 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:
jstallworth on DSKBBY8HB2PROD with RULES
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
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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)
2014–08–01, Amendment 39–17825 (79
FR 23900, April 29, 2014), and adding
the following new AD:
■
2017–24–07 Airbus: Amendment 39–19111;
Docket No. FAA–2017–0476; Product
Identifier 2016–NM–110–AD.
(a) Effective Date
This AD is effective January 5, 2018.
(b) Affected ADs
This AD replaces AD 2014–08–01,
Amendment 39–17825 (79 FR 23900, April
29, 2014) (‘‘AD 2014–08–01’’).
(c) Applicability
This AD applies to Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–211,
–212, –214, –231, –232, and –233 airplanes;
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes;
certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Reason
This AD was prompted by an investigation
that showed that when a certain combination
of target/proximity sensor serial numbers is
installed on a flap interconnecting strut, a
‘‘target FAR’’ signal cannot be detected when
reaching the mechanical end stop of the
interconnecting strut. We are issuing this AD
to prevent an undetected flap down drive
disconnection due to an already-failed
interconnecting strut sensor, which could
result in asymmetric flap panel movement
and consequent loss of control of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection To Determine the
Part Number of the Interconnecting Struts,
With Revised Service Information
This paragraph restates the requirements of
paragraph (g) of AD 2014–08–01, with
revised service information. Within 8,000
flight hours after March 26, 2014 (the
effective date of AD 2014–03–08,
Amendment 39–17745 (79 FR 9398, February
19, 2014) (‘‘AD 2014–03–08’’)), inspect to
determine the part number of the
interconnecting struts installed on both the
left-hand (LH) and right-hand (RH) wings of
the airplane, in accordance with the
Accomplishment Instructions of Airbus
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Service Bulletin A320–27–1206, Revision 01,
dated October 10, 2011; or Airbus Service
Bulletin A320–27–1206, Revision 02, dated
November 2, 2015. A review of the airplane
maintenance records is acceptable for
determining the part number of the installed
interconnecting struts, in lieu of the
inspection, if the part number of the installed
interconnecting struts, and the part number
and the serial number of the associated target
and proximity sensor, can be conclusively
determined from that review.
Accomplishment of the requirements of
paragraph (i) of this AD terminates the
requirements of this paragraph.
(1) Airplanes on which Airbus
Modification 27956 has been embodied in
production, and on which no interconnecting
strut has been replaced with a strut having
a part number specified in figure 1 to
paragraphs (g) and (h) of this AD since the
airplane’s first flight: No further work is
required by paragraph (g) of this AD.
(2) If, during the inspection required by
paragraph (g) of this AD, any interconnecting
strut is installed with a part number specified
in figure 1 to paragraphs (g) and (h) of this
AD: Within 8,000 flight hours after March 26,
2014 (the effective date of AD 2014–03–08),
determine the part number and the serial
number of the associated target and
proximity sensor.
(i) For airplanes having conditions
specified in paragraphs (g)(2)(i)(A),
(g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this
AD: Before further flight, replace the
interconnecting strut with a serviceable unit,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1206, Revision 01, dated October 10,
2011; or Airbus Service Bulletin A320–27–
1206, Revision 02, dated November 2, 2015.
For the purposes of paragraph (g) of this AD,
a serviceable interconnecting strut is a unit
that has been determined to be in compliance
with the requirements of paragraph (g) of this
AD.
(A) A target part number (P/N) ABS0121–
13 or P/N 8–536–01; and
(B) A target serial number lower than 1600,
or a target serial number that is unreadable;
and
(C) A proximity sensor having P/N
ABS0121–31 or P/N 8–372–04; and
(D) A proximity sensor having a serial
number between C59198 and C59435, or a
serial number (S/N) C500000 or higher.
(ii) For a target having S/N 1600 or higher
and target P/N ABS0121–13 or P/N 8–536–
01: Within 8,000 flight hours after March 26,
2014 (the effective date of AD 2014–03–08),
re-identify the interconnecting strut, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1206, Revision 01, dated October 10,
2011; or Airbus Service Bulletin A320–27–
1206, Revision 02, dated November 2, 2015.
BILLING CODE 4910–13–P
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(h) Retained Parts Installation Prohibition,
With No Changes
jstallworth on DSKBBY8HB2PROD with RULES
This paragraph restates the requirements of
paragraph (h) of AD 2014–08–01, with no
changes. As of March 26, 2014 (the effective
date of AD 2014–03–08), no person may
install an interconnecting strut with a part
number specified in figure 1 to paragraphs (g)
and (h) of this AD, on any airplane, except
for parts identified in paragraph (g)(2)(ii) of
this AD, provided that the actions in
paragraph (g)(2)(ii) are done. As of the
effective date of this AD, comply with the
requirements of paragraph (l) of this AD in
lieu of the requirements of this paragraph.
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(i) New Requirements of This AD: Inspection
To Determine the Part Number of the
Interconnecting Struts and the Part Number
and Serial Number of the Associated Target
and Proximity Sensor
Within 24 months after the effective date
of this AD, accomplish the actions specified
in paragraphs (i)(1) and (i)(2) of this AD, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1206, Revision 02, dated November 2,
2015. Accomplishment of the actions
specified in this paragraph terminates the
requirements of paragraph (g) of this AD. In
lieu of doing the actions specified in
paragraphs (i)(1) and (i)(2) of this AD, a
review of the airplane maintenance records is
acceptable for determining the part number
of the installed interconnecting struts and the
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part number and the serial number of the
associated target and proximity sensor, if the
part number and serial numbers can be
conclusively determined from that review.
(1) Inspect to determine the part number of
the interconnecting struts installed on both
the LH and RH wings on the airplane.
(2) If an interconnecting strut is installed
with a part number specified in figure 2 to
paragraphs (i)(2), (k), and (l) of this AD,
identify the part number and the serial
number of the associated target and
proximity sensor; and for the target and
proximity sensor part number and serial
number combination specified in paragraph
(j) of this AD, within the compliance times
specified in paragraph (j) of this AD, do the
actions specified in paragraph (j) of this AD
for that interconnecting strut.
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in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1206, Revision 02, dated November 2,
2015.
(B) If any discrepancy is found, before
further flight, replace the interconnecting
strut with a serviceable unit, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–27–1206,
Revision 02, dated November 2, 2015.
(2) If the target serial number is 1600 or
higher (with any proximity sensor part
number and serial number): Within 24
months after the effective date of this AD,
re-identify the interconnecting strut, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1206, Revision 02, dated November 2,
2015.
(k) Additional Provisions of This AD
(1) Airplanes on which Airbus
Modification 27956 has been embodied in
production, and on which no interconnecting
strut with a part number identified in figure
2 to paragraphs (i)(2), (k), and (l) of this AD
has been installed since the airplane’s first
flight, are not affected by the requirements of
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paragraph (i) of this AD, except for those
manufacturer serial numbers specified in
figure 3 to paragraph (k)(1) of this AD.
Airplanes having manufacturer serial
numbers specified in figure 3 to paragraph
(k)(1) of this AD are affected by the
requirements of paragraph (i) of this AD.
(2) For an airplane that has already been
inspected before the effective date of this AD
as specified in the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1206, dated January 28, 2011; or Revision
01, dated October 10, 2011: Within the
compliance time specified in paragraph (i) of
this AD, accomplish the additional work
specified in and in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1206, Revision 02,
dated November 2, 2015, unless it is
determined that no interconnecting strut
with a part number specified in figure 2 to
paragraphs (i)(2), (k), and (l) of this AD is
installed on that airplane. A review of
airplane maintenance records is acceptable to
make this determination, provided the part
number can be conclusively identified from
that review.
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(j) New Requirements of This AD:
Replacement or Re-Identification
(1) If the target serial number is lower than
1600 or is unreadable, and the proximity
sensor part number is P/N ABS0121–31 or
P/N 8–372–04 with a serial number between
S/N C59198 and C59435, or S/N C500000 or
higher: Before further flight, do the actions
specified by paragraph (j)(1)(i) or (j)(1)(ii) of
this AD. For the purposes of paragraph (j) of
this AD, a serviceable interconnecting strut is
a unit that has been determined to be in
compliance with the requirements of
paragraphs (i) and (j) of this AD.
(i) Replace the interconnecting strut with a
serviceable unit, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1206, Revision 02,
dated November 2, 2015.
(ii) Do a general visual inspection of the
flap down drive to detect discrepancies, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1206, Revision 02, dated November 2,
2015.
(A) If no discrepancy is found, within 50
flight cycles after the inspection, replace the
interconnecting strut with a serviceable unit,
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Figure 3 to paragraph (k)(l) of this AD -Additional affected manufacturer serial
numbers
Airplane model
Affected manufacturer serial numbers
1857
1861
1865
1867
1868
1871
1873
1874
1877
1879
1883
1885
1888
1889
1891
1892
1894
1895
1896
1898
1899
1900
1902
1903
1904
1906
1907
1909
1910
1911
1913
1914
1915
1917
1918
1920
1922
1924
1927
1929
1931
1933
1935
1937
1940
1942
1944
1945
1948
1949
1951
1954
1957
1958
1961
1964
1965
1968
1969
1973
1975
1979
1981
1983
1987
1819
1820
1824
1826
1831
1833
1837
1839
1841
1844
1846
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jstallworth on DSKBBY8HB2PROD with RULES
BILLING CODE 4910–13–C
(m) Credit for Previous Actions
(l) New Requirement of This AD: Parts
Installation Limitations
As of the effective date of this AD, no
person may install, on any airplane, an
interconnecting strut with a part number
specified in figure 2 to paragraphs (i)(2), (k),
and (l) of this AD, unless it is in compliance
with the requirements of this AD.
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before March
26, 2014 (the effective date of AD 2014–03–
08), using Airbus Service Bulletin A320–27–
1206, dated January 28, 2011, and if
additional work since March 26, 2014 (the
effective date of AD 2014–03–08) has been
VerDate Sep<11>2014
14:57 Nov 30, 2017
Jkt 244001
PO 00000
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accomplished using Airbus Service Bulletin
A320–27–1206, Revision 01, dated October
10, 2011.
(n) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
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A319 series
airplanes
1860
1864
A320 series
airplanes
1858
Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations
(3) The following service information was
approved for IBR on January 5, 2018.
(i) Airbus Service Bulletin A320–27–1206,
Revision 02, dated November 2, 2015.
(ii) Reserved.
(4) The following service information was
approved for IBR on March 26, 2014 (79 FR
9398, February 19, 2014).
(i) Airbus Service Bulletin A320–27–1206,
Revision 01, dated October 10, 2011.
(ii) Reserved.
(5) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(6) You may view this service information
at the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0113, dated June 15, 2016, for related
information. This MCAI may be found in the
AD docket on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2017–0476.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW.,
Renton, Washington 98057–3356; telephone
425–227–1405; fax 425–227–1149.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.
jstallworth on DSKBBY8HB2PROD with RULES
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 (o)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(ii) AMOCs approved previously for AD
2014–08–01 are approved as AMOCs for the
corresponding provisions of paragraphs (g)
and (h) of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
[Docket No. FAA–2017–0708; Product
Identifier 2017–NM–035–AD; Amendment
39–19113; AD 2017–24–09]
(p) 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.
VerDate Sep<11>2014
14:57 Nov 30, 2017
Jkt 244001
Issued in Renton, Washington, on
November 16, 2017.
Chris Spangenberg,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–25557 Filed 11–30–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2016–20–
11, which applied to certain Airbus
Model A300 B4–600, B4–600R, and F4–
600R series airplanes, and Model A300
C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes); and Airbus Model
A310 series airplanes. AD 2016–20–11
required repetitive inspections of the
external area of the aft cargo door sill
beam for cracking, repetitive inspections
for fatigue cracking of the cargo door sill
SUMMARY:
PO 00000
Frm 00007
Fmt 4700
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56865
beam, lock fitting, and torsion box plate,
and repair if necessary. This new AD
retains the inspections for cracking, and
repair if necessary; and requires
reinforcement of the aft cargo door sill
beam area. This AD was prompted by
the development of a reinforcement
modification of the aft cargo door sill
beam area, which constitutes
terminating action for the repetitive
inspections. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective January 5,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 2, 2014 (79 FR 34403, June 17,
2014).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of January 3, 2017 (81 FR
85837, November 29, 2016).
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@
airbus.com; Internet https://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
It is also available on the Internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0708.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0708; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
E:\FR\FM\01DER1.SGM
01DER1
]]>Agencies
[Federal Register Volume 82, Number 230 (Friday, December 1, 2017)]
[Rules and Regulations]
[Pages 56859-56865]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-25557]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 /
Rules and Regulations
[[Page 56859]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0476; Product Identifier 2016-NM-110-AD; Amendment
39-19111; AD 2017-24-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2014-08-01,
which applied to all Airbus Model A318, A319, A320, and A321 series
airplanes. AD 2014-08-01 required an inspection for part numbers of the
interconnecting struts and, for affected interconnecting struts,
identification of the part and serial numbers of the associated target
and proximity sensors and replacement or re-identification of the flap
interconnecting strut if necessary. This AD continues to require an
inspection to verify the interconnecting strut part number. This AD
also provides a new compliance time and an additional inspection for
previously inspected airplanes. This AD was prompted by an
investigation that showed that when a certain combination of target/
proximity sensor serial numbers is installed on a flap interconnecting
strut, a ``target FAR'' signal cannot be detected when reaching the
mechanical end stop of the interconnecting strut. We are issuing this
AD to address the unsafe condition on these products.
DATES: This AD is effective January 5, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 5,
2018.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of March
26, 2014 (79 FR 9398, February 19, 2014).
ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet
https://www.airbus.com. You may view this referenced service information
at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of this material at the FAA,
call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0476.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0476; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057-3356; telephone 425-227-1405; fax
425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2014-08-01, Amendment 39-17825 (79 FR 23900,
April 29, 2014) (``AD 2014-08-01''). AD 2014-08-01 applied to all
Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM
published in the Federal Register on May 19, 2017 (82 FR 22918).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0113, dated June 15, 2016 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus Model A318, A319, A320, and A321 series
airplanes. The MCAI states:
The flap interconnecting strut is a safety device of the High
Lift System which acts as an alternative load path from one flap
surface to another in case of a flap drive system disconnection. In
such a failure case, the installed proximity sensors provide
information to the slat flap control computer (SFCC) and the
operation of the flap drive system is inhibited.
An engineering investigation showed that, when a certain
combination of target/sensor serial number (s/n) is installed on a
flap interconnecting strut, a ``target FAR'' signal cannot be
detected when reaching the mechanical end stop of the
interconnecting strut.
This condition, if not corrected, could cause a flap down drive
disconnection to remain undetected, due to an already-failed
interconnecting strut sensor, potentially resulting in asymmetric
flap panel movement and consequent loss of control of the aeroplane.
To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A320-27-1206 and SB A320-57-1164, to provide
identification and replacement instructions for struts that have a
certain target/sensor s/n combination installed. Aeroplanes on which
modification (mod) 27956 had been accomplished in production were
identified as not affected by the unsafe condition. Consequently,
EASA issued [EASA] AD 2012-0012 [which corresponds to FAA AD 2014-
08-01] to require accomplishment of these inspections and corrective
actions.
Since that [EASA] AD was issued, Airbus has informed EASA about
a batch of aeroplanes that were delivered with pre-mod 27956 Part
Number (P/N) flap interconnecting strut(s) installed, but declared
to be in post-mod configuration in the Aircraft Inspection Report.
Airbus SB A320-57-1202 has been issued to provide instructions to
verify the interconnecting strut P/N, and to update aircraft
documentation.
In addition, to ensure that all pre-mod parts are checked and
corrected as required, SB A320-27-1206 was revised to include a
wider range of P/N of affected interconnecting struts.
For the reasons described above, this [EASA] AD retains the
requirements of EASA
[[Page 56860]]
AD 2012-0012, which is superseded, expands the Applicability [adds
affected part numbers], changes the compliance time and requires an
additional inspection for aeroplanes that have already been
inspected.
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-2017-
0476.
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. United Airlines and the Air Line
Pilots Association, International supported the NPRM.
Request To Add Additional Identification Steps
Delta Airlines (DAL) requested that additional identification steps
be required in the NPRM to ensure that the affected parts are correctly
identified. DAL stated that figure 1 to paragraphs (g) and (h) of the
proposed AD contains part numbers for affected interconnecting struts.
DAL commented that a review of its records from inspections conducted
during compliance with AD 2014-08-01 determined that other part numbers
were possible. DAL stated that it has had at least one instance of a
part with the part number D5757032200000A.
DAL stated that figure 2 to paragraphs (i)(2), (k), and (l) of the
proposed AD adds the provision that additional alphanumeric characters
may exist. DAL commented that while the NPRM removes some of the
ambiguity that existed in AD 2014-08-01, a review of Airbus's Aircraft
Illustrated Parts Catalog (AIPC) does not show any parts with a
``letter'' suffix. DAL provided a photo that showed that the part
number appears to ``wrap'' (to the next line) on the part. DAL stated
that this ``wrapping'' condition has led to confusion in identifying
the parts.
DAL stated that per the Airbus AIPC Front Matter, the 13th, 14th,
and 15th characters are controlled in specific ways. DAL also stated
that the 13th and 14th characters are expected to be ``00'' and are
used to fill out 12-digit base numbers on the part installed during
production. DAL stated that the 15th character is a paint code
designator and found the use of a paint code designator unusual on a
part that is not viewable or expected to be painted to match an air
carrier paint scheme. DAL commented that it believes the AD should be
updated to show 00A, 00B, or the list of true possibilities, and the
XXX allowance creates a significant number of possible part numbers
that DAL must identify as prohibited.
We agree to clarify the requirement to identify affected parts.
Regarding the characters in the part number, identifying the last three
characters are not required to identify a discrepant part; only the
first twelve base numbers are required. Therefore, we do not agree to
revise this AD to include a complete list of all possible combinations
of these characters.
We acknowledge the commenter's concern about the ``wrapping''
condition for part identification. However, in the photo provided by
the commenter only the last three characters are ``wrapped.'' As stated
previously, the last three characters are not required to identify a
discrepant part.
Formatting Change to a Figure
Figure 3 to paragraph (k)(1) of this AD has been reformatted to
clarify affected manufacturer serial numbers.
Records Review
We have determined that a review of maintenance records is
acceptable for complying with the actions specified in paragraphs
(i)(1) and (i)(2) of this AD, provided the part number of the installed
interconnecting struts and the part number and the serial number of the
associated target and proximity sensor can be conclusively determined
from that review. We have revised paragraph (i) of this AD accordingly.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-27-1206, Revision 02, dated
November 2, 2015. The service information describes procedures for an
inspection to determine the part number of the installed
interconnecting struts and the part number and serial number of the
associated target and proximity sensors, and procedures for replacement
and re-identification of the interconnecting struts. 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 1,032 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection and replacement 8 work-hours x $85 per hour $0 $680 $701,760
(retained actions from AD 2014-08- = $680.
01).
Inspection and replacement (new 15 work-hours x $85 per 0 1,275 1,315,800
action). hour = $1,275.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable 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
[[Page 56861]]
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
Regulatory Findings
We determined that this 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)
2014-08-01, Amendment 39-17825 (79 FR 23900, April 29, 2014), and
adding the following new AD:
2017-24-07 Airbus: Amendment 39-19111; Docket No. FAA-2017-0476;
Product Identifier 2016-NM-110-AD.
(a) Effective Date
This AD is effective January 5, 2018.
(b) Affected ADs
This AD replaces AD 2014-08-01, Amendment 39-17825 (79 FR 23900,
April 29, 2014) (``AD 2014-08-01'').
(c) Applicability
This AD applies to Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, -231, -232, and -233
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes; certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by an investigation that showed that when a
certain combination of target/proximity sensor serial numbers is
installed on a flap interconnecting strut, a ``target FAR'' signal
cannot be detected when reaching the mechanical end stop of the
interconnecting strut. We are issuing this AD to prevent an
undetected flap down drive disconnection due to an already-failed
interconnecting strut sensor, which could result in asymmetric flap
panel movement and consequent loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection To Determine the Part Number of the
Interconnecting Struts, With Revised Service Information
This paragraph restates the requirements of paragraph (g) of AD
2014-08-01, with revised service information. Within 8,000 flight
hours after March 26, 2014 (the effective date of AD 2014-03-08,
Amendment 39-17745 (79 FR 9398, February 19, 2014) (``AD 2014-03-
08'')), inspect to determine the part number of the interconnecting
struts installed on both the left-hand (LH) and right-hand (RH)
wings of the airplane, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1206, Revision 01,
dated October 10, 2011; or Airbus Service Bulletin A320-27-1206,
Revision 02, dated November 2, 2015. A review of the airplane
maintenance records is acceptable for determining the part number of
the installed interconnecting struts, in lieu of the inspection, if
the part number of the installed interconnecting struts, and the
part number and the serial number of the associated target and
proximity sensor, can be conclusively determined from that review.
Accomplishment of the requirements of paragraph (i) of this AD
terminates the requirements of this paragraph.
(1) Airplanes on which Airbus Modification 27956 has been
embodied in production, and on which no interconnecting strut has
been replaced with a strut having a part number specified in figure
1 to paragraphs (g) and (h) of this AD since the airplane's first
flight: No further work is required by paragraph (g) of this AD.
(2) If, during the inspection required by paragraph (g) of this
AD, any interconnecting strut is installed with a part number
specified in figure 1 to paragraphs (g) and (h) of this AD: Within
8,000 flight hours after March 26, 2014 (the effective date of AD
2014-03-08), determine the part number and the serial number of the
associated target and proximity sensor.
(i) For airplanes having conditions specified in paragraphs
(g)(2)(i)(A), (g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this
AD: Before further flight, replace the interconnecting strut with a
serviceable unit, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-27-1206, Revision 01, dated October
10, 2011; or Airbus Service Bulletin A320-27-1206, Revision 02,
dated November 2, 2015. For the purposes of paragraph (g) of this
AD, a serviceable interconnecting strut is a unit that has been
determined to be in compliance with the requirements of paragraph
(g) of this AD.
(A) A target part number (P/N) ABS0121-13 or P/N 8-536-01; and
(B) A target serial number lower than 1600, or a target serial
number that is unreadable; and
(C) A proximity sensor having P/N ABS0121-31 or P/N 8-372-04;
and
(D) A proximity sensor having a serial number between C59198 and
C59435, or a serial number (S/N) C500000 or higher.
(ii) For a target having S/N 1600 or higher and target P/N
ABS0121-13 or P/N 8-536-01: Within 8,000 flight hours after March
26, 2014 (the effective date of AD 2014-03-08), re-identify the
interconnecting strut, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1206, Revision 01,
dated October 10, 2011; or Airbus Service Bulletin A320-27-1206,
Revision 02, dated November 2, 2015.
BILLING CODE 4910-13-P
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(h) Retained Parts Installation Prohibition, With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2014-08-01, with no changes. As of March 26, 2014 (the effective
date of AD 2014-03-08), no person may install an interconnecting
strut with a part number specified in figure 1 to paragraphs (g) and
(h) of this AD, on any airplane, except for parts identified in
paragraph (g)(2)(ii) of this AD, provided that the actions in
paragraph (g)(2)(ii) are done. As of the effective date of this AD,
comply with the requirements of paragraph (l) of this AD in lieu of
the requirements of this paragraph.
(i) New Requirements of This AD: Inspection To Determine the Part
Number of the Interconnecting Struts and the Part Number and Serial
Number of the Associated Target and Proximity Sensor
Within 24 months after the effective date of this AD, accomplish
the actions specified in paragraphs (i)(1) and (i)(2) of this AD, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-27-1206, Revision 02, dated November 2, 2015.
Accomplishment of the actions specified in this paragraph terminates
the requirements of paragraph (g) of this AD. In lieu of doing the
actions specified in paragraphs (i)(1) and (i)(2) of this AD, a
review of the airplane maintenance records is acceptable for
determining the part number of the installed interconnecting struts
and the part number and the serial number of the associated target
and proximity sensor, if the part number and serial numbers can be
conclusively determined from that review.
(1) Inspect to determine the part number of the interconnecting
struts installed on both the LH and RH wings on the airplane.
(2) If an interconnecting strut is installed with a part number
specified in figure 2 to paragraphs (i)(2), (k), and (l) of this AD,
identify the part number and the serial number of the associated
target and proximity sensor; and for the target and proximity sensor
part number and serial number combination specified in paragraph (j)
of this AD, within the compliance times specified in paragraph (j)
of this AD, do the actions specified in paragraph (j) of this AD for
that interconnecting strut.
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(j) New Requirements of This AD: Replacement or Re-Identification
(1) If the target serial number is lower than 1600 or is
unreadable, and the proximity sensor part number is P/N ABS0121-31
or P/N 8-372-04 with a serial number between S/N C59198 and C59435,
or S/N C500000 or higher: Before further flight, do the actions
specified by paragraph (j)(1)(i) or (j)(1)(ii) of this AD. For the
purposes of paragraph (j) of this AD, a serviceable interconnecting
strut is a unit that has been determined to be in compliance with
the requirements of paragraphs (i) and (j) of this AD.
(i) Replace the interconnecting strut with a serviceable unit,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-27-1206, Revision 02, dated November 2, 2015.
(ii) Do a general visual inspection of the flap down drive to
detect discrepancies, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1206, Revision 02,
dated November 2, 2015.
(A) If no discrepancy is found, within 50 flight cycles after
the inspection, replace the interconnecting strut with a serviceable
unit, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-27-1206, Revision 02, dated November 2, 2015.
(B) If any discrepancy is found, before further flight, replace
the interconnecting strut with a serviceable unit, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-27-1206, Revision 02, dated November 2, 2015.
(2) If the target serial number is 1600 or higher (with any
proximity sensor part number and serial number): Within 24 months
after the effective date of this AD, re-identify the interconnecting
strut, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-27-1206, Revision 02, dated November 2, 2015.
(k) Additional Provisions of This AD
(1) Airplanes on which Airbus Modification 27956 has been
embodied in production, and on which no interconnecting strut with a
part number identified in figure 2 to paragraphs (i)(2), (k), and
(l) of this AD has been installed since the airplane's first flight,
are not affected by the requirements of paragraph (i) of this AD,
except for those manufacturer serial numbers specified in figure 3
to paragraph (k)(1) of this AD. Airplanes having manufacturer serial
numbers specified in figure 3 to paragraph (k)(1) of this AD are
affected by the requirements of paragraph (i) of this AD.
(2) For an airplane that has already been inspected before the
effective date of this AD as specified in the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1206, dated January
28, 2011; or Revision 01, dated October 10, 2011: Within the
compliance time specified in paragraph (i) of this AD, accomplish
the additional work specified in and in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1206,
Revision 02, dated November 2, 2015, unless it is determined that no
interconnecting strut with a part number specified in figure 2 to
paragraphs (i)(2), (k), and (l) of this AD is installed on that
airplane. A review of airplane maintenance records is acceptable to
make this determination, provided the part number can be
conclusively identified from that review.
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(l) New Requirement of This AD: Parts Installation Limitations
As of the effective date of this AD, no person may install, on
any airplane, an interconnecting strut with a part number specified
in figure 2 to paragraphs (i)(2), (k), and (l) of this AD, unless it
is in compliance with the requirements of this AD.
(m) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before
March 26, 2014 (the effective date of AD 2014-03-08), using Airbus
Service Bulletin A320-27-1206, dated January 28, 2011, and if
additional work since March 26, 2014 (the effective date of AD 2014-
03-08) has been accomplished using Airbus Service Bulletin A320-27-
1206, Revision 01, dated October 10, 2011.
(n) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International
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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 (o)(2) of this AD. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(ii) AMOCs approved previously for AD 2014-08-01 are approved as
AMOCs for the corresponding provisions of paragraphs (g) and (h) of
this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0113, dated June 15, 2016, for related
information. This MCAI may be found in the AD docket on the Internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2017-0476.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356;
telephone 425-227-1405; fax 425-227-1149.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
January 5, 2018.
(i) Airbus Service Bulletin A320-27-1206, Revision 02, dated
November 2, 2015.
(ii) Reserved.
(4) The following service information was approved for IBR on
March 26, 2014 (79 FR 9398, February 19, 2014).
(i) Airbus Service Bulletin A320-27-1206, Revision 01, dated
October 10, 2011.
(ii) Reserved.
(5) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
(6) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on November 16, 2017.
Chris Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2017-25557 Filed 11-30-17; 8:45 am]
BILLING CODE 4910-13-P
