Airworthiness Directives; Airbus Airplanes, 22918-22922 [2017-10134]
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Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), 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 ACO, send it to the
attention of the person identified in
paragraph (k)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (i)(2)
of this AD: For service information that
contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(4)(ii)
of this AD apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
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(2) Where Boeing Alert Service Bulletin
757–53A0101, dated November 8, 2016,
specifies to contact Boeing for appropriate
action and identifies that action as ‘‘RC’’
(Required for Compliance): Before further
flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
Issued in Renton, Washington, on May 10,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10033 Filed 5–18–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
[Docket No. FAA–2017–0476; Directorate
Identifier 2016–NM–110–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2014–08–
01, for all Airbus Model A318, A319,
A320, and A321 series airplanes. AD
2014–08–01 currently requires 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. Since we issued AD 2014–
08–01, we have determined that certain
airplanes must be inspected to verify the
interconnecting strut part number. This
proposed AD would add airplanes to the
applicability. We are proposing this AD
to address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by July 3, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
(k) Related Information
11.43 and 11.45, by any of the following
(1) For more information about this AD,
methods:
contact Muoi Vuong, Aerospace Engineer,
• Federal eRulemaking Portal: Go to
Airframe Branch, ANM–120L, FAA, Los
https://www.regulations.gov. Follow the
Angeles ACO, 3960 Paramount Boulevard,
instructions for submitting comments.
Lakewood, CA 90712–4137; phone: 562–627–
• Fax: 202–493–2251.
5205; fax: 562–627–5210; email:
• Mail: U.S. Department of
Muoi.Vuong@faa.gov.
Transportation, Docket Operations, M–
(2) For service information identified in
30, West Building Ground Floor, Room
this AD, contact Boeing Commercial
W12–140, 1200 New Jersey Avenue SE.,
Airplanes, Attention: Contractual & Data
Washington, DC 20590.
Services (C&DS), 2600 Westminster Blvd.,
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18:29 May 18, 2017
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• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
SUMMARY:
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FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
425–227–1405; fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2017–0476; Directorate Identifier
2016–NM–110–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
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Discussion
On April 7, 2014, we issued AD 2014–
08–01, Amendment 39–17825 (79 FR
23900, April 29, 2014) (‘‘AD 2014–08–
01’’), for all Airbus Model A318, A319,
A320, and A321 series airplanes. AD
2014–08–01 superseded AD 2014–03–
08, Amendment 39–17745 (79 FR 9398,
February 19, 2014) (‘‘AD 2014–03–08’’).
AD 2014–08–01 was prompted by a
report that an investigation 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 it reaches the mechanical end
stop of the interconnecting strut. AD
2014–08–01 requires an inspection to
determine the part number of the
interconnecting struts installed on the
wings, identifying the part number and
the serial number of the associated
target and proximity sensor if
applicable, and replacing or reidentifying the flap interconnecting
strut if applicable. We issued AD 2014–
08–01 to correct the definition of a
serviceable interconnecting strut.
Since we issued AD 2014–08–01, we
received a report that airplanes were
delivered with pre-modification 27956
part number installed on the flap
interconnecting strut(s), but declared to
be in post-modification configuration in
the Aircraft Inspection Report. We have
determined that certain airplanes must
be inspected to verify the
interconnecting strut part number.
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
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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
2014–03–08] 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
AD 2012–0012, which is superseded,
expands the Applicability, 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.
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 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 sensor,
and 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.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
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22919
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 1,032 airplanes of U.S. registry.
The actions required by AD 2014–08–
01, and retained in this proposed AD,
take about 8 work-hours per product, at
an average labor rate of $85 per workhour. Required parts cost about $0 per
product. Based on these figures, the
estimated cost of the actions that are
required by AD 2014–08–01 is $680 per
product.
We also estimate that it would take
about 15 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $0 per product.
Based on these figures, we estimate the
cost of this proposed AD on U.S.
operators to be $1,315,800, or $1,275 per
product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
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.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
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Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2014–08–01, Amendment 39–17825 (79
FR 23900, April 29, 2014), and adding
the following new AD:
■
Airbus: Docket No. FAA–2017–0476;
Directorate Identifier 2016–NM–110–AD.
(a) Comments Due Date
We must receive comments by July 3, 2017.
(b) Affected ADs
This AD replaces AD 2014–08–01,
Amendment 39–17825 (79 FR 23900, April
29, 2014) (‘‘AD 2014–08–01’’).
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(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 a report that an
investigation showed that when a certain
combination of a target/proximity sensor
serial numbers is installed on a flap
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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 detect and
correct a latent failure of the 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
which has been determined to be in
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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.
FIGURE 1 TO PARAGRAPHS (g) AND (h)
OF
THIS AD—INTERCONNECTING
STRUT PART NUMBERS
Interconnecting strut part numbers
D5757030500000
D5757030500100
D5757030500200
D5757030500600
D5757030500800
D5757030501000
D5757030501200
D5757032200000
(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 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.
(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
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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.
FIGURE 2 TO PARAGRAPHS (i)(2), (k),
AND (l) OF THIS AD—AFFECTED
INTERCONNECTING STRUTS
[XXX signifies any alpha-numeric combination.
It may be possible to find units with only XX]
D57570305000XXX
D57570305001XXX
D57570305002XXX
D57570305006XXX
D57570305008XXX
D57570305010XXX
D57570305012XXX
D57570322000XXX
(j) New Requirements of This AD:
Replacement or Reidentification
(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
required 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 which 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, reidentify 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
is 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
1, 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 2,
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.
FIGURE 3 TO PARAGRAPH (k)(1) OF THIS AD—ADDITIONAL AFFECTED MANUFACTURER SERIAL NUMBERS
Airplane model—
Affected Manufacturer Serial Numbers—
A320 series airplanes ......................................................................................
sradovich on DSK3GMQ082PROD with PROPOSALS
A319 series airplanes ......................................................................................
(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
VerDate Sep<11>2014
18:29 May 18, 2017
Jkt 241001
1857
1864
1871
1879
1889
1895
1900
1906
1911
1917
1924
1933
1942
1949
1958
1968
1979
1819
1831
1841
1853
1870
1880
1890
1908
1925
1943
specified in figure 2 to paragraphs (i)(2), (k),
and (l) of this AD, unless it has been
modified in accordance with the
requirements of this AD.
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
1858
1865
1873
1883
1891
1896
1902
1907
1913
1918
1927
1935
1944
1951
1961
1969
1981
1820
1833
1844
1855
1872
1882
1893
1912
1934
1947
1860
1867
1874
1885
1892
1898
1903
1909
1914
1920
1929
1937
1945
1954
1964
1973
1983
1824
1837
1846
1863
1875
1884
1897
1916
1936
1861
1868
1877
1888
1894
1899
1904
1910
1915
1922
1931
1940
1948
1957
1965
1975
1987
1826
1839
1851
1866
1876
1886
1901
1923
1938
(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–
E:\FR\FM\19MYP1.SGM
19MYP1
22922
Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules
08), using Airbus Service Bulletin A320–27–
1206, dated January 28, 2011, and if
additional work has been accomplished
using Airbus Service Bulletin A320–27–1206,
Revision 01, dated October 10, 2011.
sradovich on DSK3GMQ082PROD with PROPOSALS
(n) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone 425–227–1405; fax 425–227–
1149. Information may be emailed to: 9ANM-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 Branch, ANM–
116, Transport Airplane Directorate, 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 service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
VerDate Sep<11>2014
18:29 May 18, 2017
Jkt 241001
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on May 11,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10134 Filed 5–18–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2017–0210; Airspace
Docket No. 17–AGL–10]
Proposed Amendment of Class D and
E Airspace; Kenosha, WI
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
modify Class D airspace, Class E
airspace designated as a surface area,
and Class E airspace extending upward
from 700 feet above the surface, and
remove Class E airspace designated as
an extension of Class D airspace at
Kenosha Regional Airport, Kenosha, WI.
The FAA is proposing this action due to
the decommissioning of the Kenosha
VHF omnidirectional range (VOR)
facilities, which provided navigation
guidance for portions of the affected
routes. This action would enhance the
safety and management of instrument
flight rules (IFR) operations at this
airport. Additionally, the airport name
and geographic coordinates would be
adjusted in the Class E airspace
extending upward from 700 feet above
the surface to coincide with the FAA’s
aeronautical database.
DATES: Comments must be received on
or before July 3, 2017.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590; telephone 202–
366–9826, or 1–800–647–5527. You
must identify FAA Docket No. FAA–
2017–0210; Airspace Docket No. 17–
AGL–10 at the beginning of your
comments. You may also submit
SUMMARY:
PO 00000
Frm 00019
Fmt 4702
Sfmt 4702
comments through the Internet at https://
www.regulations.gov. You may review
the public docket containing the
proposal, any comments received, and
any final disposition in person in the
Dockets Office between 9:00 a.m. and
5:00 p.m., Monday through Friday,
except federal holidays.
FAA Order 7400.11A, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
online at https://www.faa.gov/air_traffic/
publications/. For further information,
you can contact the Airspace Policy
Group, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC, 20591;
telephone: 202–267–8783. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
information on the availability of FAA
Order 7400.11A at NARA, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federalregulations/ibr_locations.html.
FAA Order 7400.11, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
FOR FURTHER INFORMATION CONTACT:
Jeffrey Claypool, Federal Aviation
Administration, Operations Support
Group, Central Service Center, 10101
Hillwood Parkway, Fort Worth, TX,
76177; telephone 817–222–5711.
SUPPLEMENTARY INFORMATION:
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it would
amend Class D airspace, Class E
airspace designated as a surface area,
and Class E airspace extending upward
from 700 feet above the surface, as well
as remove Class E airspace designated as
an extension to Class D airspace at
Kenosha Regional Airport, Kenosha, WI,
to enhance the safety and management
of IFR operations at this airport..
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
E:\FR\FM\19MYP1.SGM
19MYP1
]]>Agencies
[Federal Register Volume 82, Number 96 (Friday, May 19, 2017)]
[Proposed Rules]
[Pages 22918-22922]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10134]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0476; Directorate Identifier 2016-NM-110-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-08-
01, for all Airbus Model A318, A319, A320, and A321 series airplanes.
AD 2014-08-01 currently requires 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. Since we issued AD 2014-08-01, we
have determined that certain airplanes must be inspected to verify the
interconnecting strut part number. This proposed AD would add airplanes
to the applicability. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by July 3, 2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus,
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 425-227-
1405; fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0476;
Directorate Identifier 2016-NM-110-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
[[Page 22919]]
Discussion
On April 7, 2014, we issued AD 2014-08-01, Amendment 39-17825 (79
FR 23900, April 29, 2014) (``AD 2014-08-01''), for all Airbus Model
A318, A319, A320, and A321 series airplanes. AD 2014-08-01 superseded
AD 2014-03-08, Amendment 39-17745 (79 FR 9398, February 19, 2014) (``AD
2014-03-08''). AD 2014-08-01 was prompted by a report that an
investigation 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 it reaches the
mechanical end stop of the interconnecting strut. AD 2014-08-01
requires an inspection to determine the part number of the
interconnecting struts installed on the wings, identifying the part
number and the serial number of the associated target and proximity
sensor if applicable, and replacing or re-identifying the flap
interconnecting strut if applicable. We issued AD 2014-08-01 to correct
the definition of a serviceable interconnecting strut.
Since we issued AD 2014-08-01, we received a report that airplanes
were delivered with pre-modification 27956 part number installed on the
flap interconnecting strut(s), but declared to be in post-modification
configuration in the Aircraft Inspection Report. We have determined
that certain airplanes must be inspected to verify the interconnecting
strut part number.
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-
03-08] 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 AD 2012-0012, which is superseded, expands the
Applicability, 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.
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 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 sensor, and 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.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 1,032 airplanes of U.S.
registry.
The actions required by AD 2014-08-01, and retained in this
proposed AD, take about 8 work-hours per product, at an average labor
rate of $85 per work-hour. Required parts cost about $0 per product.
Based on these figures, the estimated cost of the actions that are
required by AD 2014-08-01 is $680 per product.
We also estimate that it would take about 15 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $0 per
product. Based on these figures, we estimate the cost of this proposed
AD on U.S. operators to be $1,315,800, or $1,275 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and
[[Page 22920]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2014-08-01, Amendment 39-17825 (79 FR 23900, April 29, 2014), and
adding the following new AD:
Airbus: Docket No. FAA-2017-0476; Directorate Identifier 2016-NM-
110-AD.
(a) Comments Due Date
We must receive comments by July 3, 2017.
(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 a report that an investigation showed
that when a certain combination of a 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 detect
and correct a latent failure of the 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 which 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.
Figure 1 to Paragraphs (g) and (h) of This AD--Interconnecting Strut
Part Numbers
------------------------------------------------------------------------
Interconnecting strut part numbers
-------------------------------------------------------------------------
D5757030500000
D5757030500100
D5757030500200
D5757030500600
D5757030500800
D5757030501000
D5757030501200
D5757032200000
------------------------------------------------------------------------
(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 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.
(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
[[Page 22921]]
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.
Figure 2 to Paragraphs (i)(2), (k), and (l) of This AD--Affected
Interconnecting Struts
[XXX signifies any alpha-numeric combination. It may be possible to find
units with only XX]
-------------------------------------------------------------------------
D57570305000XXX
D57570305001XXX
D57570305002XXX
D57570305006XXX
D57570305008XXX
D57570305010XXX
D57570305012XXX
D57570322000XXX
------------------------------------------------------------------------
(j) New Requirements of This AD: Replacement or Reidentification
(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
required 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 which 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 is 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 1, 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 2, 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.
Figure 3 to Paragraph (k)(1) of This AD--Additional Affected Manufacturer Serial Numbers
----------------------------------------------------------------------------------------------------------------
Airplane model-- Affected Manufacturer Serial Numbers--
----------------------------------------------------------------------------------------------------------------
A320 series airplanes........................... 1857 1858 1860 1861
1864 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
A319 series airplanes........................... 1819 1820 1824 1826
1831 1833 1837 1839
1841 1844 1846 1851
1853 1855 1863 1866
1870 1872 1875 1876
1880 1882 1884 1886
1890 1893 1897 1901
1908 1912 1916 1923
1925 1934 1936 1938
1943 1947
----------------------------------------------------------------------------------------------------------------
(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
has been modified in accordance 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-
[[Page 22922]]
08), using Airbus Service Bulletin A320-27-1206, dated January 28,
2011, and if additional work 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 Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington
98057-3356; telephone 425-227-1405; fax 425-227-1149. 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 Branch, ANM-116, Transport
Airplane Directorate, 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 service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on May 11, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10134 Filed 5-18-17; 8:45 am]
BILLING CODE 4910-13-P
