Nachrichten für Luftfahrer 2016 Teil 2 (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2016-136 38144 Braunschweig
EASA AD 2016-0094 vom 19.05.2016 Fax: +49-531-2355-5298
email: ad@LBA.de
CZECH SPORT AIRCRAFT 27.05.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: CZECH SPORT AIRCRAFT a.s.
Hersteller: Czech Sport Aircraft a.s.
Muster: PS-28 Cruiser
Baureihen: PS-28 Cruiser
Werknummern: Alle bis C0556.
Betroffen sind Flugzeuge, die mit einem BRP-Powertrain GmbH & Co. KG
Rotax 912 ULS2 Triebwerk ausgestattet sind.
Gerätenummer: EASA.A.546
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2016-0094 vom 19.05.2016
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 2016-136 geführt.
Betrifft:
(ATA 72) Engine - Engine Cylinder Head - Inspection / Replacement
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen Luftfahr-
zeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen werden,
wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2016-0094 vom 19.05.2016 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
gültige 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-2016-136 Seite 1 von 1 231/2016
EASA AD No.: 2016-0094
Airworthiness Directive
AD No.: 2016-0094
Issued: 19 May 2016
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EC) 216/2008 on behalf of the European Union, its Member States and of the European third
countries that participate in the activities of EASA under Article 66 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 (EC) 216/2008, Article 14(4) exemption].
Design Approval Holder’s Name: Type/Model designation(s):
CZECH SPORT AIRCRAFT a.s. PS-28 Cruiser aeroplanes
Effective Date: 02 June 2016
TCDS Number(s): EASA.A.546
Foreign AD: Note applicable
Supersedure: None
ATA 72 – Engine – Engine Cylinder Head – Inspection / Replacement
Manufacturer(s):
Czech Sport Aircraft a.s.
Applicability:
PS-28 Cruiser aeroplanes, all manufacturer serial numbers up to C0556 inclusive, if equipped with
BRP-Powertrain GmbH & Co. KG Rotax 912 ULS2 engines.
Reason:
A design change of the engine cylinder heads was introduced by BRP-Powertrain in March 2013,
which modifies the engine/aeroplane interfaces by substituting the previous cylinder head
temperature (CHT) measurement (limit temperature 135°C) with a coolant temperature (CT)
measurement (limit temperature 120°C). The design change was communicated on 15 May 2013 by
BRP-Powertrain Service Instruction (SI) 912-020R7/914-022R7 (single document), but was not
identified by a change of the engine model designation or of the engine Part Number (P/N), but only
through the cylinder head P/N and the position of the temperature sensor.
Consequently, engines with the new cylinder heads (installed during production or replaced
in-service during maintenance) may be installed on an aeroplane without concurrent modification
of that aeroplane. In this case, the coolant temperature with a maximum engine operating limit of
120°C (valid for engines operated with water diluted glycol coolant) is displayed on a CHT indicator
with a typical limit marking (red radial/range) of more than 120°C.
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EASA AD No.: 2016-0094
This condition, if not detected and corrected, will prevent the pilot to identify coolant limit
exceedances, with subsequent loss of coolant (120°C is the boiling temperature of the coolant),
which could lead to engine in-flight shut-down, possibly resulting in a forced landing, with
consequent damage to the aeroplane and injury to occupants.
EASA issued AD 2015-0240 to address this potential unsafe condition on certificated Rotax 912
engines (TCDS EASA.E.121), requiring to determine the actual engine configuration and, depending
on findings, engine re-identification and (depending on TC or STC holder installation) modification
of the affected aeroplane.
PS-28 Cruiser aeroplanes may be equipped with a Rotax 912 ULS2 engine, certified as part of the
aeroplane type design, on which the same unsafe condition may exist or develop. Consequently,
Czech Sport Aircraft a.s. issued Service Bulletin (SB) No. SB-CR-033 to provide instructions to inspect
and, depending on findings, modify the affected PS-28 Cruiser aeroplanes.
For the reason described above, this AD requires a one-time inspection to determine the actual
engine configuration and, depending on findings, re-identification of the engine (including those
operated with waterless coolant) and modification of the aeroplane.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Within 3 months after the effective date of this AD, accomplish the actions as required by this AD.
(1) Inspect the engine to determine whether a cylinder head, having P/N 413185 is installed on
cylinder head position 2/3. A review of aircraft and/or engine maintenance records is
acceptable to make the determination as required by this paragraph, provided those records
can be relied upon for that purpose.
(2) If, during the inspection as required by paragraph (1) of this AD, a cylinder head having
P/N 413185 is found installed on position 2 or 3, accomplish the actions specified in paragraphs
(2.1) or (2.2) of this AD, as applicable.
(2.1) For an engine with cylinder heads, having P/N 413185, installed on both positions 2 and 3,
change the designation of that engine in accordance with the instructions of Czech Sport
Aircraft a.s. SB-CR-033.
(2.2) For an engine with one cylinder head, having P/N 413185, installed on a single position (2
or 3), replace the cylinder head installed on the unchanged position (3 or 2, as applicable)
with a cylinder head having P/N 413185, and concurrently change the designation of that
engine in accordance with the instructions of Czech Sport Aircraft a.s. SB-CR-033.
(3) Concurrently with the corrective action as required by paragraph (2) of this AD, inspect the
engine temperature indicating instrument designation and its displayed operating limits in the
aeroplane cockpit in accordance with the instructions of Czech Sport Aircraft a.s. SB-CR-033.
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 3
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EASA AD No.: 2016-0094
(4) If, during the inspection as required by paragraph (3) of this AD, an engine CHT indicating
instrument or an engine temperature instrument with the maximum temperature limit higher
than 120°C is detected, accomplish all the corrective actions in accordance with the instructions
of Czech Sport Aircraft a.s. SB-CR-033.
Ref. Publications:
Czech Sport Aircraft SB-CR-033, original issue dated 18 March 2016.
The use of later approved revisions of this document 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. This AD was posted on 14 April 2016 as PAD 16-054 for consultation until 12 May 2016. No
comments were received during the consultation period.
3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,
Certification Directorate. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements in this AD, please
contact: Czech Sport Aircraft a.s., Na Záhonech 212, 686 04 Kunovice, Czech Republic,
Telephone: +420 576 514 032, Fax: +420 576 519 394, Email: office@czechsportaircraft.com.
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 3 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2016-137 38144 Braunschweig
TC AD CF-2016-16 vom 20.05.2016 Fax: +49-531-2355-5298
email: ad@LBA.de
BOMBARDIER 27.05.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Bombardier Inc.
Hersteller: Bombardier Inc.
Muster: DHC-8
Baureihen: DHC-8-400, DHC-8-401 und DHC-8-402
Werknummern: 4001 und 4003 bis 4325
Betroffen sind Flugzeuge, die mit einem "Main Landing Gear (MLG) Retract
Actuator Rod End" mit der Part-Nummer (P/N) P3A2750 oder P3A2750-1
ausgerüstet sind.
Gerätenummer: 2868, EASA.IM.A.191, TC TCDS A-142
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
TC AD CF-2016-16 vom 20.05.2016
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 2016-137 geführt.
Betrifft:
(ATA 32) Landing Gear – Main Landing Gear – Retract Actuator Rod End Cracking
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen Luftfahr-
zeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen werden,
wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
TC AD CF-2016-16 vom 20.05.2016 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
gültige 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-2016-137 Seite 1 von 1 234/2016
TP 7245E
1 of 2
AD Number: CF-2016-16
AIRWORTHINESS DIRECTIVE
This Airworthiness Directive (AD) is issued pursuant to Canadian Aviation Regulation (CAR) 521.427.
No person shall conduct a take-off or permit a take-off to be conducted in an aircraft that is in their legal
custody and control, unless the requirements of CAR 605.84 pertaining to ADs are met. Standard 625 -
Aircraft Equipment and Maintenance Standards Appendix H provides information concerning alternative
means of compliance (AMOC) to ADs.
Number: Effective Date:
CF-2016-16 3 June 2016
ATA: Type Certificate:
32 A-142
Subject:
Landing Gear – Main Landing Gear – Retract Actuator Rod End Cracking
Applicability:
Bombardier Inc. DHC-8-400 series, models -400, -401 and -402, serial numbers 4001, 4003 thru 4325,
equipped with main landing gear (MLG) retract actuator rod end part number (P/N) P3A2750 or
P3A2750-1.
Compliance:
As indicated below, unless already accomplished.
Background:
There has been a single reported case of a cracked MLG retract actuator rod end in service. A supplier
disclosure letter and subsequent Bombardier analysis indicate that the MLG retract actuator rod end P/N
P3A2750 and P3A2750-1 may develop fatigue cracking. This condition, if not corrected, could lead to left
hand (LH) or right hand (RH) MLG collapse.
This AD mandates the inspection and replacement of the LH and RH MLG retract actuator rod ends P/N
P3A2750 and P3A2750-1.
Corrective Actions:
A. Within 100 Flight Cycles (FC) from the effective date of this AD, verify the part number of the LH and
RH MLG retract actuator rod end installed onboard the aeroplane in accordance with the
accomplishment instructions contained in Bombardier Service Bulletin (SB) 84-32-142, Initial Issue,
dated 4 May 2016, or later revisions approved by the Chief, Continuing Airworthiness, Transport
Canada. If rod end P/N P3A6460 is installed on the LH and RH MLG, no further action is required.
Verification of the part number can be done through an inspection of the aeroplane or a review of the
aeroplanes records.
B. For rod ends P3A2750 or P3A2750-1 that have accumulated more than 6000 FC from the effective
day of this AD:
1. Within 100 FC from the effective date of this AD, perform the initial Liquid Penetrant Inspection
(LPI) in accordance with the accomplishment instructions contained in Bombardier SB 84-32-142,
Initial Issue, dated 4 May 2016, or later revisions approved by the Chief, Continuing
Airworthiness, Transport Canada:
a. If a crack is found, remove rod end P/N P3A2750 or P3A2750-1 and replace with rod end P/N
P3A6460 before further flight in accordance with the accomplishment instructions contained
CF-2016-16 2 of 2
in Bombardier SB 84-32-142, Initial Issue, dated 4 May 2016, or later revisions approved by
the Chief, Continuing Airworthiness, Transport Canada.
b. If no crack is found, repeat the LPI on the rod end at intervals not to exceed 600 FC.
2. Within 1800 FC from the initial inspection date, remove and replace rod end P/N P3A2750 or
P3A2750-1 with rod end P/N P3A6460 in accordance with the accomplishment instructions
contained in Bombardier (SB) 84-32-142, Initial Issue, dated 4 May 2016, or later revisions
approved by the Chief, Continuing Airworthiness, Transport Canada. The accumulated flight
cycles on rod end P/N P3A2750 or P3A2750-1 shall not exceed 10450 FC.
C. For rod ends P/N P3A2750 or P3A2750-1 that have accumulated less than or equal to 6000 FC from
the effective date of this AD:
1. Within 600 FC from the effective date of this AD, perform the initial Liquid Penetrant Inspection
(LPI) in accordance with the accomplishment instructions contained in Bombardier (SB)
84-32-142, Initial Issue, dated 4 May 2016, or later revisions approved by the Chief, Continuing
Airworthiness, Transport Canada.
a. If a crack is found, remove rod end P/N P3A2750 or P3A2750-1 and replace with rod end P/N
P3A6460 before further flight in accordance with the accomplishment instructions contained
in Bombardier SB 84-32-142, Initial Issue, dated 4 May 2016, or later revisions approved by
the Chief, Continuing Airworthiness, Transport Canada.
b. If no crack is found, repeat the LPI on the rod end at intervals not to exceed 600 FC.
2. Within 1800 FC from the initial inspection date, remove and replace rod end P/N P3A2750 or
P3A2750-1 with rod end P/N P3A6460 in accordance with the accomplishment instructions
contained in Bombardier SB 84-32-142, Initial Issue, dated 4 May 2016, or later revisions
approved by the Chief, Continuing Airworthiness, Transport Canada.
D. As of the effective date of this AD, no person shall install a MLG retract actuator rod end P/N
P3A2750 or P3A2750-1 on DHC-8 Series 400 aeroplanes.
E. Installation of rod end P/N P3A6460 on both LH side and RH side MLG is considered as terminating
action for this AD.
F. If it is not possible to complete all the instructions in SB 84-32-142 because of the configuration of the
aeroplane, contact the Q Series Technical Help Desk in Toronto at telephone 1-514-855-8500 or Toll
Free North America 1-844-272-2720 or facsimile (416) 375-4539 or e-mail:
thd.qseries@aero.bombardier.com for an approved disposition/repair and incorporate the
disposition/repair, before further flight. The approved disposition/repair must specifically reference this
AD.
Authorization:
For the Minister of Transport,
ORIGINAL SIGNED BY
Robin Lau
Acting Chief, Continuing Airworthiness
Issued on 20 May 2016
Contact:
Craig. McAllister, Continuing Airworthiness, Ottawa, telephone 1-888-663-3639, facsimile 613-996-9178
or e-mail AD-CN@tc.gc.ca or any Transport Canada Centre.
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2016-138 38144 Braunschweig
EASA AD 2016-0095 vom 19.05.2016 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS 27.05.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS
Hersteller: Airbus
Muster: A380
Baureihen: A380-841, A380-842 und A380-861
Werknummern: Alle
Gerätenummer: EASA.A.110
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2016-0095 vom 19.05.2016
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 2016-138 geführt.
Betrifft:
(ATA 57) Wings – Flap Parts – Identification / Inspection [Wrong material]
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen Luftfahr-
zeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen werden,
wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2016-0095 vom 19.05.2016 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
gültige 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-2016-138 Seite 1 von 1 232/2016
EASA AD No.: 2016-0095
Airworthiness Directive
AD No.: 2016-0095
Issued: 19 May 2016
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EC) 216/2008 on behalf of the European Union, its Member States and of the European third
countries that participate in the activities of EASA under Article 66 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 (EC) 216/2008, Article 14(4) exemption].
Design Approval Holder’s Name: Type/Model designation(s):
AIRBUS A380 aeroplanes
Effective Date: 02 June 2016
TCDS Number(s): EASA.A.110
Foreign AD: Not applicable
Supersedure: None
ATA 57 – Wings – Flap Parts – Identification / Inspection [Wrong material]
Manufacturer(s):
Airbus
Applicability:
Airbus A380-841, A380-842 and A380-861 aeroplanes, all manufacturer serial numbers (MSN).
Reason:
Following an Airbus quality control review on the final assembly line, it was discovered that
non-conforming aluminium alloy had been used to manufacture several structural parts located on
the middle and outboard flaps.
This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane.
To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A380-57-8111 to
provide instructions to identify and inspect the potentially affected parts.
For the reasons described above, this AD requires identification of the potentially affected middle
and outboard flap parts, a one-time Special Detailed Inspection (SDI) to identify which material they
are made of and, depending on findings, replacement with serviceable parts.
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EASA AD No.: 2016-0095
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Note 1: Appendix 1 of this AD lists the potentially affected middle (Table 1) and outboard (Table 2)
flaps by serial number (s/n).
(1) Within 3 months after the effective date of this AD, identify the s/n of the left hand (LH) and
right hand (RH) middle and outboard flaps installed on the aeroplane.
A review of aeroplane delivery and/or maintenance records is acceptable for identifying the
installed flaps, provided those records can be relied upon for that purpose and the s/n of the
affected parts can be positively identified from that review.
Note 2: Airbus SB A380-57-8111 lists the batch of affected LH and RH middle and outboard flaps and
the corresponding aeroplane MSN on which these parts were installed on production line. That
MSN list is for information only, as it cannot be excluded that an affected middle or outboard flap
has been removed from an aeroplane and later re-installed on another aeroplane.
(2) For each middle and outboard flap, identified as required by paragraph (1) of this AD, and
having a s/n as listed in Appendix 1 of this AD, within 7 years or 4 300 flight cycles (FC),
whichever occurs first, accumulated by the affected flap from the date as defined in Appendix 1
of this AD, depending on the affected flap s/n, accomplish a SDI of the affected flap parts, in
accordance with the instructions of Airbus SB A380-57-8111.
(3) If, during the SDI as required by paragraph (2) of this AD, a part manufactured from
non-conforming material is detected, within 30 days after the SDI as required by paragraph (2)
of this AD, contact Airbus for replacement instructions and within the compliance time
indicated in those instructions, accomplish the replacement accordingly.
(4) From the effective date of this AD, it is allowed to install on an aeroplane a middle or outboard
flap having a s/n listed in Appendix 1 of this AD, provided that, prior to installation, it has been
determined that the part is a serviceable part as defined in Note 3 of this AD.
Note 3: For the purpose of this AD, a serviceable middle or outboard flap is a part that is not listed
by s/n in Appendix 1 of this AD, or has a s/n listed in Appendix 1 of this AD but has passed an SDI in
accordance with the instructions of Airbus SB A380-57-8111.
Ref. Publications:
Airbus SB A380-57-8111 original issue, dated 07 January 2016.
The use of later approved revisions of this document 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.
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 6
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