Nachrichten für Luftfahrer 2018 Teil 2 (weicht ggf. von Druckversion ab)
AIRWORTHINESS
FAA DIRECTIVE
Aviation Safety
www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html
2018-22-10 The Boeing Company: Amendment 39-19483; Docket No. FAA-2018-0510; Product
Identifier 2017-NM-115-AD.
(a) Effective Date
This AD is effective December 12, 2018.
(b) Affected ADs
(1) This AD replaces AD 2016-04-16, Amendment 39-18410 (81 FR 12806, March 11, 2016)
(“AD 2016-04-16”).
(2) This AD affects AD 2002-13-10, Amendment 39-12798 (67 FR 45053, July 8, 2002) (“AD
2002-13-10”).
(3) This AD affects AD 2003-07-14, Amendment 39-13110 (68 FR 17544, April 10, 2003) (“AD
2003-07-14”).
(4) This AD affects AD 2008-06-21 R1, Amendment 39-16100 (74 FR 61504, November 25,
2009) (“AD 2008-06-21 R1”).
(5) This AD affects AD 2011-11-05, Amendment 39-16704 (76 FR 31462, June 1, 2011) (“AD
2011-11-05”).
(c) Applicability
This AD applies to all The Boeing Company airplanes identified in paragraphs (c)(1) and (c)(2)
of this AD, certificated in any category.
(1) Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10),
DC-10-40, and DC-10-40F airplanes.
(2) Model MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by a fuel system review conducted by the manufacturer. We are issuing
this AD to address the potential of ignition sources inside fuel tanks, which, in combination with
flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Restatement of Paragraph (g) of AD 2016-04-16, With No Changes
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This paragraph restates the requirements of paragraph (g) of AD 2016-04-16, with no changes.
Except as provided by paragraph (h) of this AD: As of 48 months after April 15, 2016 (the effective
date of AD 2016-04-16), no person may operate any airplane affected by this AD unless an amended
type certificate or supplemental type certificate that incorporates the design features and requirements
described in paragraphs (g)(1) through (g)(4) of this AD has been approved by the Manager, Los
Angeles ACO Branch, FAA, and those design features are installed on the airplane to meet the
criteria specified in section 25.981(a) and (d) of the Federal Aviation Regulations (14 CFR 25.981(a)
and (d), at Amendment 25-125
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgFAR.nsf/0/339DAEE3E0A6379D862574CF
00641951?OpenDocument)). For airplanes on which Boeing-installed auxiliary fuel tanks are
removed, the actions specified in this AD for the auxiliary fuel tanks are not required.
(1) For all airplanes: Each electrically powered alternating current (AC) fuel pump installed in
any fuel tank that normally empties during flight and each pump that is partially covered by a
lowering fuel level–such as main tanks, center wing tanks, auxiliary fuel tanks installed by the
airplane manufacturer, and tail tanks–must have a protective device installed to detect electrical faults
that can cause arcing and burn through of the fuel pump housing and pump electrical connector. The
same device must shut off the pump by automatically removing electrical power from the pump when
such faults are detected. When a fuel pump is shut off resulting from detection of an electrical fault,
the device must stay latched off, until the fault is cleared through maintenance action and the pump is
verified safe for operation.
(2) For airplanes with a 2-person flightcrew: Additional design features, if not originally installed
by the airplane manufacturer, must be installed to meet 3 criteria: To detect a running fuel pump in a
tank that is normally emptied during flight, to provide an indication to the flightcrew that the tank is
empty, and to automatically shut off that fuel pump. The prospective pump indication and shutoff
system must automatically shut off each pump in case the flightcrew does not shut off a pump
running dry in an empty tank within 60 seconds after each fuel tank is emptied. An airplane flight
manual supplement (AFMS) that includes flightcrew manual pump shutoff procedures in the
Limitations section of the AFMS must be submitted to the Los Angeles ACO Branch, FAA, for
approval.
(3) For airplanes with a 3-person flightcrew: Additional design features, if not originally installed
by the airplane manufacturer, must be installed to detect when a fuel pump in a tank that is normally
emptied during flight is running in an empty fuel tank, and to provide an indication to the flightcrew
that the tank is empty. The flight engineer must manually shut off each pump running dry in an empty
tank within 60 seconds after the tank is emptied. The AFMS Limitations section must be revised to
specify that this pump shutoff must be done by the flight engineer.
(4) For all airplanes with tanks that normally empty during flight: Separate means must be
provided to detect and shut off a pump that was previously commanded to be shut off automatically
or manually but remained running in an empty tank during flight.
(h) Restatement of Paragraph (h) of AD 2016-04-16, With No Changes
This paragraph restates the provisions of paragraph (h) of AD 2016-04-16, with no changes. In
lieu of doing the requirements of paragraph (g) of this AD, do the applicable actions specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this AD.
(1) For MD-11 and MD-11F airplanes: Do the actions specified in paragraphs (h)(1)(i) and
(h)(1)(ii) of this AD.
(i) As of 48 months after April 15, 2016 (the effective date of AD 2016-04-16), change the fuel
pump control and indication system wiring, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin MD11-28-137, dated June 24, 2014.
(ii) Prior to or concurrently with accomplishing the actions specified in paragraph (h)(1)(i) of this
AD: Replace the fuel pump control relays with fault current detectors, and change the fuel tank
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boost/transfer pump wire termination, in accordance with Accomplishment Instructions of Boeing
Alert Service Bulletin MD11-28A133, dated June 5, 2014.
(2) For Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-
10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F airplanes: Do the actions specified in
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) As of 48 months after April 15, 2016 (the effective date of AD 2016-04-16), change the fuel
pump control and indication system wiring, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin DC10-28-256, dated June 24, 2014.
(ii) Prior to or concurrently with accomplishing the actions specified in paragraph (h)(2)(i) of this
AD: Replace the fuel pump control relays with fault current detectors, and change the fuel tank
boost/transfer pump wire termination, in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin DC10-28A253, dated June 5, 2014.
(3) For all airplanes: Within 30 days after accomplishing the actions required by paragraph (h)(1)
or (h)(2) of this AD, or within 30 days after April 15, 2016 (the effective date of AD 2016-04-16),
whichever occurs later, revise the maintenance or inspection program, as applicable, to incorporate
the Critical Design Configuration Control Limitations (CDCCLs), Airworthiness Limitation
Instructions (ALIs), and short-term extensions specified in Appendices B, C, and D of Boeing Trijet
Special Compliance Item (SCI) Report MDC-02K1003, Revision M, dated July 25, 2014. The initial
compliance time for accomplishing the actions specified in the ALIs is at the later of the times
specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. Revising the maintenance or inspection
program required by this paragraph terminates the requirements in paragraphs (g) and (h) of AD
2008-06-21 R1.
(i) At the applicable time specified in Appendix C of Boeing Trijet SCI Report MDC-02K1003,
Revision M, dated July 25, 2014, except as provided by Appendix D of Boeing Trijet SCI Report
MDC-02K1003, Revision M, dated July 25, 2014.
(ii) Within 30 days after accomplishing the actions required by paragraph (h)(1) or (h)(2) of this
AD, as applicable; or within 30 days after April 15, 2016 (the effective date of AD 2016-04-16);
whichever occurs later.
(i) Restatement of Paragraph (i) of AD 2016-04-16, With No Changes
This paragraph restates the requirements of paragraph (i) of AD 2016-04-16, with no changes. If
the option in paragraph (h)(3) of this AD is accomplished: After the maintenance or inspection
program has been revised as provided by paragraph (h)(3) of this AD, no alternative actions (e.g.,
inspections), intervals, or CDCCLs may be used unless the actions, intervals, or CDCCLs are
approved as an alternative method of compliance (AMOC) in accordance with the procedures
specified in paragraph (m) of this AD.
(j) Restatement of Paragraph (j) of AD 2016-04-16, With Additional AD Reference and
Clarification of Provisions
This paragraph restates the provisions of paragraph (j) of AD 2016-04-16, with an additional AD
reference and clarification of the provisions. Accomplishment of the actions specified in paragraphs
(h)(1), (h)(2), and (h)(3) of this AD, as applicable, extends the 18-month interval for the repetitive
inspections and tests required by paragraph (a) of AD 2002-13-10; the 18-month interval for the
repetitive inspections required by paragraph (a) of AD 2003-07-14; and the 18-month interval for the
repetitive inspections required by paragraph (j) of AD 2011-11-05; to 24-month intervals for pumps
affected by those ADs, regardless if the pump is installed in a tank that normally empties, provided
the remaining actions required by those three ADs have been accomplished.
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(k) New Provision of This AD: Optional Terminating Action
For airplanes on which the actions specified in paragraph (h)(1)(ii) or (h)(2)(ii) have been done:
Replacing the electrical connectors or fuel pump housing in accordance with the Accomplishment
Instructions of Boeing Service Bulletin DC10-28-264, dated May 15, 2015; or Boeing Service
Bulletin MD11-28-146, dated May 15, 2015, as applicable; terminates the repetitive inspections and
tests required by paragraph (a) of AD 2002-13-10, paragraph (a) of AD 2003-07-14, and paragraph
(j) of AD 2011-11-05.
(l) New Provision of This AD: Optional Revision
(1) In lieu of accomplishing the revision specified in paragraph (h)(3) of this AD: Within the
compliance time specified in paragraph (h)(3) of this AD, operators may revise the maintenance or
inspection program, as applicable, to incorporate the CDCCLs, ALIs, and short-term extensions
specified in Appendices B, C, and D of Boeing Trijet Special Compliance Item Report MDC-
02K1003, Revision R, dated May 9, 2018. The initial compliance time for accomplishing the actions
specified in the ALIs is at the later of the times specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this
AD. Revising the maintenance or inspection program specified in this paragraph terminates the
requirements in paragraphs (g) and (h) of AD 2008-06-21 R1.
(i) At the applicable time specified in Appendix C of Boeing Trijet Special Compliance Item
Report MDC-02K1003, Revision R, dated May 9, 2018, except as provided by Appendix D of
Boeing Trijet Special Compliance Item Report MDC-02K1003, Revision R, dated May 9, 2018.
(ii) Within 30 days after accomplishing the actions required by paragraph (h)(1) or (h)(2) of this
AD, as applicable; or within 30 days after the effective date of this AD; whichever occurs later.
(2) If the optional revision specified in paragraph (l)(1) of this AD is accomplished: After the
maintenance or inspection program has been revised as provided by paragraph (1)(1) of this AD, no
alternative actions (e.g., inspections), intervals, or CDCCLs may be used unless the actions, intervals,
or CDCCLs are approved as an AMOC in accordance with the procedures specified in paragraph (m)
of this AD.
(m) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles ACO Branch, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the manager of the certification office, send it to the attention of the
person identified in paragraph (n) of this AD. Information may be emailed to: 9-ANM-LAACO-
AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a
principal inspector, the manager of the local flight standards district office/certificate holding district
office.
(3) An AMOC that provides an acceptable level of safety may be used for any repair,
modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes
Organization Designation Authorization (ODA) that has been authorized by the Manager, Los
Angeles ACO Branch, FAA, 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) For service information that contains steps that are labeled as Required for Compliance (RC),
the provisions of paragraphs (m)(4)(i) and (m)(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
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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.
(n) Related Information
For more information about this AD, contact Serj Harutunian, Aerospace Engineer, Propulsion
Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5254; fax: 562-627-5210; email: serj.harutunian@faa.gov.
(o) 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 the AD specifies otherwise.
(3) The following service information was approved for IBR on December 12, 2018.
(i) Boeing Service Bulletin DC10-28-264, dated May 15, 2015.
(ii) Boeing Service Bulletin MD11-28-146, dated May 15, 2015.
(iii) Boeing Trijet Special Compliance Item Report MDC-02K1003, Revision R, including
Appendices A through D, dated May 9, 2018.
(4) The following service information was approved for IBR on April 15, 2016 (81 FR 12806,
March 11, 2016).
(i) Boeing Alert Service Bulletin DC10-28A253, dated June 5, 2014.
(ii) Boeing Service Bulletin DC10-28-256, dated June 24, 2014.
(iii) Boeing Alert Service Bulletin MD11-28A133, dated June 5, 2014.
(iv) Boeing Service Bulletin MD11-28-137, dated June 24, 2014.
(v) Boeing Trijet Special Compliance Item Report MDC-02K1003, Revision M, including
Appendices A through D, dated July 25, 2014.
(5) For service information identified in this AD, contact Boeing Commercial Airplanes,
Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal
Beach, CA 90740-5600; telephone: 562-797-1717; internet: https://www.myboeingfleet.com.
(6) You may view this service information at the FAA, Transport Standards Branch, 2200 South
216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-
231-3195.
(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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on October 24, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
11
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2014-003R2 38144 Braunschweig
EASA AD 2018-0233R1 vom 28.11.2018 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS 30.11.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS S.A.S.
Hersteller: Airbus (vormals Airbus Industrie)
Muster: A319, A320, A321
Baureihen: A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132,
A319-133,
A320-211, A320-212, A320-214, A320-215, A320-216, A320-231, A320-232,
A320-233,
A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231
und A321-232
Werknummern: Alle
Ausgenommen sind:
(1) A319 Flugzeuge, an denen die Airbus Modifikation (Mod) 161306 bei der
Flugzeug-Herstellung eingerüstet worden ist und
(2) A319 CJ Flugzeuge, an denen weder die Airbus Mod 160001 bei der
Flugzeug-Herstellung eingerüstet worden ist noch die Maßnahmen gemäß
Airbus Service Bulletin (SB) A320-57-1193 (Mod 160080) durchgeführt worden
sind und
(3) A320 Flugzeuge, an denen die Airbus Mod 161271 bei der Flugzeug-
Herstellung eingerüstet worden ist.
Gerätenummer: 2846, EASA.A.064
Revisionsstand:
Diese LTA ersetzt D-2014-003R1 vom 07.11.2018
Airworthiness Directive der ausländischen Behörde:
EASA AD 2018-0233R1 vom 28.11.2018
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 02/2003 übernommen und sind somit ebenfalls Airworthiness
Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2014-003R2 geführt.
Betrifft:
(ATA 53) Fuselage - Cargo Compartment Fitting Brackets, Track and Rivet Holes - Inspection / Repair
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301 5.i) und M.A.303 dür-
fen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genom-
men werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2018-0233R1 vom 28.11.2018 herausgegeben oder per Entscheidung Nr. 02/2003 übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsanweisun-
gen direkt in der Bundesrepublik Deutschland gültig und bedürfen keiner Umsetzung durch das Luftfahrt-
Bundesamt.
Mit Hilfe dieser Übersichtsseite veröffentlicht das Luftfahrt-Bundesamt ebenfalls die über § 14 Abs. 2 direkt
gültigen Lufttüchtigkeitsanweisungen der EASA in den Nachrichten für Luftfahrer und im Internet unter
www2.LBA.de/LTAs/. Dieser Service dient reinen Informationszwecken und liegt keinem Verwaltungsver-
fahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2014-003R2 Seite 1 von 1 556/2018
EASA AD No.: 2018-0233R1
Airworthiness Directive
AD No.: 2018-0233R1
Issued: 28 November 2018
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EU) 2018/1139 on behalf of the European Union, its Member States and of the European third
countries that participate in the activities of EASA under Article 129 of that Regulation.
This AD is issued in accordance with Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 Annex I, Part M.A.301, the
continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which
an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [Regulation (EU) 1321/2014 Annex I,
Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (EU) 2018/1139, Article 71 exemption].
Design Approval Holder’s Name: Type/Model designation(s):
AIRBUS A319, A320 and A321 aeroplanes
Effective Date: Revision 01: 05 December 2018
Original issue: 09 November 2018
TCDS Number(s): EASA.A.064
Foreign AD: Not applicable
Supersedure: This AD revises EASA AD 2018-0233 dated 26 October 2018, which superseded
EASA AD 2013-0310 dated 20 December 2013.
ATA 53 – Fuselage – Cargo Compartment Fitting Brackets, Tack and Rivet Holes –
Inspection / Repair
Manufacturer(s):
Airbus, formerly Airbus Industrie
Applicability:
Airbus A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132 and A319-133,
aeroplanes, all manufacturer serial numbers, except those on which Airbus modification (mod)
161306 has been embodied in production, and except A319 CJ aeroplanes that have not embodied
Airbus mod 160001 in production, and Airbus Service Bulletin (SB) A320-57-1193 (mod 160080) in
service.
Airbus A320-211, A320-212, A320-214, A320-215, A320-216, A320-231, A320-232, A320-233,
A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231 and A321-232
aeroplanes, all manufacturer serial numbers, except those on which Airbus mod 161271 has been
embodied in production.
Definitions:
For the purpose of this AD, the following definitions apply:
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EASA AD No.: 2018-0233R1
The inspection SB: Airbus SB A320-53-1257 Revision (Rev.) 02.
The applicable modification SB: Airbus SB A320-53-1261 Rev. 04, SB A320-53-1360 (any revision),
SB A320-53-1364 and SB A320-53-1365, as applicable.
A319 CJ: A319 (Corporate Jet) aeroplanes on which Airbus mod 28238, mod 28162 and mod 28342
have been embodied in production.
A319 PAX: A319 aeroplanes, which are not A319 CJ.
Reason:
During a full scale fatigue test, several broken frames in the cargo compartment area between
Frame (FR) 50 and FR63 have been found, especially on the cargo floor support fittings and open
tack holes on left hand (LH) side.
This condition, if not detected and corrected, could affect the structural integrity of the aeroplane.
To address this unsafe condition, Airbus issued SB A320-53-1257, providing inspection instructions,
and SB A320-53-1261, providing modification instructions.
Consequently, EASA published AD 2013-0310, requiring repetitive inspections of the frames in the
cargo compartment area and of the cargo floor support fittings and open tack holes on the LH side
and, depending on findings, accomplishment of corrective action(s). That AD also required a
modification, which constituted terminating action for the required repetitive inspections.
After that AD was issued, further analyses and widespread fatigue damage evaluations identified
the need to reduce the threshold and intervals for the repetitive inspections for certain
configurations, and Airbus issued the inspection SB accordingly. Airbus issued SB A320-53-1360,
SB A320-53-1364 and SB A320-53-1365 to supplement SB A320-53-1261, and SB Information
Transmission (SBIT) 16-0070 providing additional information. Consequently, EASA issued AD
2018-0233, retaining the requirements of EASA AD 2013-0310, which was superseded, but requiring
accomplishment of the repetitive inspections within reduced compliance times for certain
configurations. That AD also required additional work for aeroplanes that had already been
modified in accordance with the instructions of Airbus SB A320-53-1261 Rev. 02.
Since that AD was issued, it has been determined that certain A319 aeroplanes may be excluded
from the Applicability of the AD, since the calculated compliance time for the initial inspection is
beyond the applicable limit of validity.
For the reason described above, this AD is revised to reduce the Applicability.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Repetitive Inspection(s):
(1) Within the compliance time(s) as defined in Table 1 or Table 2 of Appendix 1 of this AD, as
applicable, and, thereafter, at intervals not to exceed the values as defined in Table 3 of
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EASA AD No.: 2018-0233R1
Appendix 1 of this AD, as applicable, accomplish a rototest inspection of open tack holes and
rivet holes at the cargo floor support fittings between FR50 and FR63, between Stringer (STG)
33 and STG39 (LH side only), for A320 and A321 aeroplanes, and between FR53 and FR63,
between STG33 and STG39 (LH side only), for A319 aeroplanes, in accordance with the
instructions of the inspection SB.
Corrective Action(s):
(2) If, during any inspection as required by paragraph (1) of this AD, a crack is detected, before next
flight, contact Airbus for approved repair instructions and, within the compliance time
identified in those instructions, accomplish those instructions accordingly.
Modification:
(3) Except as required by paragraph (4) of this AD, before exceeding 48 000 flight cycles (FC) or
96 000 flight hours (FH), whichever occurs first since aeroplane first flight, modify the aeroplane
in accordance with the instructions of the applicable modification SB.
Additional Work:
(4) For an aeroplane that was modified, before the effective date of this AD, in accordance with the
instructions of Airbus SB A320-53-1261 Rev. 02, within 30 days after 09 November 2018 [the
effective date of the original issue of this AD], contact Airbus for additional work instructions
and, within the compliance time specified in those instructions, accomplish the additional work
accordingly.
Credit:
(5) Modification of an aeroplane, before 09 November 2018 [the effective date of the original issue
of this AD], in accordance with the instructions of Airbus SB A320-53-1261 original issue, or
Rev. 01, or Rev. 03, is acceptable to comply with the requirements of paragraph (3) of this AD
for that aeroplane.
(6) Inspections on an aeroplane, accomplished before 09 November 2018 [the effective date of the
original issue of this AD], in accordance with the instructions of Airbus SB A320-53-1257 at
original issue or Rev. 01, are acceptable to comply with the initial requirements of paragraph (1)
of this AD for that aeroplane.
Terminating Action:
(7) Repair of an aeroplane as required by paragraph (2) of this AD does not constitutes terminating
action for the repetitive inspections as required by paragraph (1) of this AD for that aeroplane,
unless otherwise stated in the repair instructions.
(8) Modification of an aeroplane as required by paragraph (3) or (4) of this AD, as applicable,
constitutes terminating action for the repetitive inspections as required by paragraph (1) of this
AD for that aeroplane.
Ref. Publications:
Airbus SB A320-53-1257 original issue dated 21 December 2012, or Rev. 01 dated 28 April 2016, or
Rev. 02 dated 29 November 2016.
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Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2018-0233R1
Airbus SB A320-53-1261 original issue dated 21 December 2012, or Rev. 01 dated 30 June 2015, or
Rev. 02 dated 01 March 2016, or Rev. 03 dated 08 August 2016, or Rev. 04 dated 03 May 2017.
Airbus SB A320-53-1360 original issue dated 01 December 2016, or Rev. 01 dated 01 March 2018.
Airbus SB A320-53-1364 original issue dated 04 May 2018.
Airbus SB A320-53-1365 original issue dated 17 April 2018.
The use of later approved revisions of the above-mentioned documents is acceptable for
compliance with the requirements of this AD.
Remarks:
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of
Compliance for this AD.
2. The original issue of this AD was posted on 11 July 2018 as PAD 18-093 for consultation until 08
August 2018. The Comment Response Document can be found in the EASA Safety Publications
Tool, in the compressed (zipped) file attached to the record for this AD.
3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,
Certification Directorate. E-mail: ADs@easa.europa.eu.
4. Information about any failures, malfunctions, defects or other occurrences, which may be
similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on
a product, part or appliance not affected by this AD, can be reported to the EU aviation safety
reporting system.
5. For any question concerning the technical content of the requirements in this AD, please
contact: AIRBUS – Airworthiness Office – EIAS; Fax +33 5 61 93 44 51;
E-mail: account.airworth-eas@airbus.com.
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