Nachrichten für Luftfahrer 2016 Teil 2 (weicht ggf. von Druckversion ab)
EASA AD No.: 2016-0099
Table 1 – Compliance Time
Affected TR blades Compliance Time
All TR Blades, except S/N A.60.04.027, Within 36 months after the date of release to
S/N A.60.04.28, and S/N A.60.05.064 or service issued by WSK "PZL-Świdnik" S.A. after an
higher inspection and modification accomplished in
accordance with the instruction of WSK "PZL-
Świdnik" S.A. MB No. BO-60-16-77
S/N A.60.04.027 and S/N A.60.04.28 Within 36 months after the effective date of this
AD
S/N A.60.05.064 and higher Before exceeding 36 months since new (see Note
1 of this AD)
(3) If, during any inspection as required by paragraph (2) of this AD, any discrepancy is detected, as
defined in the instructions of Attachment 1 to WSK "PZL-Świdnik" S.A. MB No. BO-60-16-77,
before next flight, replace the affected TR blade with a serviceable part in accordance with the
instructions of WSK "PZL-Świdnik" S.A. MB No. BO-60-16-77 (see paragraph (5) of this AD).
(4) Replacement of a TR blade on a helicopter, as required by paragraph (3) of this AD, does not
constitute terminating action for the repetitive inspections as required by paragraph (2) of this
AD for that helicopter.
(5) From the effective date of this AD, installation of a TR blade P/N 60.02.680.00.01 on a
helicopter is allowed, provided the part meets the criteria defined in paragraph (5.1) or (5.2) of
this AD, as applicable.
(5.1) The part is released to service by WSK "PZL-Świdnik" S.A. after an inspection and
modification accomplished in accordance with the instructions of Chapter II paragraph 3.
of WSK "PZL-Świdnik" S.A. MB No. BO-60-16-77 or after a repair accomplished in
accordance with the instructions of Chapter II paragraph 4. of WSK "PZL-Świdnik" S.A. MB
No. BO-60-16-77, without any FH accumulated after that modification or repair, as
applicable.
(5.2) The feathering hinge case of the TR blade corresponds to design standard P/N
60.02.686.01.01 revision H, or subsequent, and, for used TR blade only, before
installation, the TR blade has passed an inspection in accordance with the instructions of
Attachment 1 to WSK "PZL-Świdnik" S.A. MB No. BO-60-16-77.
Ref. Publications:
WSK "PZL-Świdnik" S.A. MB No. BO-60-16-77 original issue dated 11 May 2016.
The use of later approved revisions of this document is acceptable for compliance with the
requirements of this AD.
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EASA AD No.: 2016-0099
Remarks:
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of
Compliance for this AD.
2. Based on the required actions and the compliance time, EASA have decided to issue a Final AD
with Request for Comments, postponing the public consultation process until after publication.
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:
WSK "PZL- Świdnik" S.A.
Al. Lotników Polskich 1
21-045 Świdnik, Poland
Phone: (+48) 664 424 798
E-mail: pl-customersupport@leonardocompany.com.
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2016-144 38144 Braunschweig
EASA AD 2016-0100 vom 24.05.2016 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS 31.05.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS
Hersteller: Airbus, Airbus Industrie
Muster: A300, A300-600, A310
Baureihen: Alle A300, A300-600 und A310 Baureihen
Werknummern: Alle
Gerätenummer: 2830, EASA.A.172
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2016-0100 vom 24.05.2016
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 2016-144 geführt.
Betrifft:
(ATA 53) Fuselage - Nose Landing Gear Door Hinge Bolt Assembly - Replacement (Life Limit)
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 2016-0100 vom 24.05.2016 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-2016-144 Seite 1 von 1 240/2016
EASA AD No.: 2016-0100
Airworthiness Directive
AD No.: 2016-0100
Issued: 24 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 A300, A300-600 and A310 aeroplanes
Effective Date: 07 June 2016
TCDS Number: EASA.A.0172
Foreign AD: Not applicable
Supersedure: None
ATA 53 – Fuselage – Nose Landing Gear Door Hinge Bolt Assembly – Replacement
[Life Limit]
Manufacturer(s):
Airbus (formerly Airbus Industrie)
Applicability:
Airbus A300, A310 and A300-600 aeroplanes, all Manufacturer Serial Numbers.
Reason:
An occurrence has been reported of failure of a nose landing gear (NLG) door aft hinge bolt
assembly, Part Number (P/N) A53612600000. The result of laboratory investigations revealed that
the aft hinge bolt rupture was initiated by fatigue crack development in the under head radius of
the bolt, due to the lack of radius roll over and in combination with a non-optimised design.
This condition, if not detected and corrected, could lead to in-flight loss of an aft NLG door, possibly
resulting in damage to the aeroplane and injury to persons on the ground.
Prompted by these findings, Airbus developed a new design aft hinge bolt assembly P/N
A53612713000, introduced as Airbus modification (mod) 13741, to replace the existing bolt P/N
A53612600000. Since the introduction of that mod, additional stress calculations demonstrated that
the new bolt assembly, P/N A53612713000, cannot sustain fatigue loads up to the design Limit of
Validity (LOV) of the affected aeroplanes.
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EASA AD No.: 2016-0100
To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A300-53-0397, SB
A310-53-2144 and SB A300-53-6186, to provide instructions for the repetitive replacement of the
affected post-mod 13741 P/N A53612713000 aft hinge bolts.
For the reasons described above, this AD requires the replacement of all P/N A53612600000 aft
hinge bolt assemblies, installed on the left hand (LH) and right hand (RH) NLG aft doors, with
post-mod 13741 P/N A53612713000 aft hinge bolt assemblies, and, subsequently, the
implementation of a life limit for those new bolt assemblies.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
(1) Before exceeding 10 000 flight cycles (FC) since first flight of the aeroplane, or within 2 000 FC
after the effective date of this AD, whichever occurs later, replace each P/N A53612600000 NLG
aft door hinge bolt assembly with a new hinge bolt assembly P/N A53612713000 in accordance
with the instructions of Airbus SB A300-53-0396, or SB A310-53-2142 or SB A300-53-6182, as
applicable.
(2) Within 10 000 FC after modification of an aeroplane as required by paragraph (1) of this AD,
and, thereafter, at intervals not to exceed 10 000 FC, replace each hinge bolt assembly P/N
A53612713000 with a new hinge bolt assembly in accordance with the instructions of Airbus SB
A300-53-0397, or SB A310-53-2144, or SB A300-53-6186, as applicable.
(3) After modification of an aeroplane as required by paragraph (1) of this AD, do not install an aft
hinge bolt assembly P/N A53612600000 on any aft NLG door of that aeroplane.
(4) After removal of a NLG aft hinge bolt assembly P/N A53612713000 from an aeroplane, as
required by paragraph (2) of this AD, do not install that aft hinge bolt assembly on any
aeroplane.
Ref. Publications:
Airbus SB A300-53-0396 at original issue dated 25 November 2015.
Airbus SB A300-53-0397 at original issue dated 18 January 2016.
Airbus SB A300-53-6182 at original issue dated 17 November 2015.
Airbus SB A300-53-6186 at original issue dated 18 January 2016.
Airbus SB A310-53-2142 at original issue dated 17 November 2015.
Airbus SB A310-53-2144 at original issue dated 18 January 2016.
The use of later approved revisions of these documents is acceptable for compliance with the
requirements of this AD.
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An agency of the European Union
EASA AD No.: 2016-0100
Remarks:
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of
Compliance for this AD.
2. This AD was posted on 21 March 2016 as PAD 16-046 for consultation until 18 April 2016 and
republished on 28 April 2016 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: AIRBUS – EIAW (Airworthiness Office),
E-mail: E-mail: continued.airworthiness-wb.external@airbus.com.
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An agency of the European Union
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2016-145 38144 Braunschweig
FAA AD 2016-09-13 - Amdt. 39-18511 Fax: +49-531-2355-5298
email: ad@LBA.de
BOEING 31.05.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: The Boeing Company
Hersteller: The Boeing Company
Muster: BOEING 737
Baureihen: 737-300, 737-400, 737-500
Werknummern: Gemäß Boeing Alert Service Bulletin 737-53A1339 vom 12.08.2014
Gerätenummer: 2823, EASA.IM.A.120, FAA TCDS A16WE
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2016-09-13 - Amdt. 39-18511
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 2016-145 geführt.
Betrifft:
(ATA 53) Fuselage - Upper Frames - Inspection / Repair
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
FAA AD 2016-09-13 - Amdt. 39-18511 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-2016-145 Seite 1 von 1 216/2016
[Federal Register Volume 81, Number 89 (Monday, May 9, 2016)]
[Rules and Regulations]
[Pages 27989-27992]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10524]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0246; Directorate Identifier 2014-NM-187-AD; Amendment 39-18511;
AD 2016-09-13]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company
Model 737-300, -400, and -500 series airplanes. This AD was prompted by reports of fatigue
cracking found at the left-side and right-side upper frames, at a certain area. This AD requires
repetitive medium frequency eddy current (MFEC) inspections for cracking of the left-side and right-
side upper frames, and repair (including open hole high frequency eddy current (HFEC) inspections
for cracking of fastener holes) if necessary. This AD also provides an optional preventive
modification, which terminates the repetitive inspections at the modified location. We are issuing this
AD to detect and correct fatigue cracking of the upper frame, which can grow in size and result in a
severed frame, leading to rapid decompression and consequent reduced structural integrity of the
airplane.
DATES: This AD is effective June 13, 2016.
The Director of the Federal Register approved the incorporation by reference of a certain
publication listed in this AD as of June 13, 2016.
ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes,
Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; 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. It is also available on the Internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2015-0264.
1
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for
and locating Docket No. FAA-2015-0246; or in person at the Docket Management Facility between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD,
the regulatory evaluation, any comments received, and other information. The address for the Docket
Office (phone: 800-647-5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer, Airframe
Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount
Boulevard, Lakewood, California 90712-4137; phone: 562-627-5324; fax: 562-627-5210; email:
galib.abumeri@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD
that would apply to certain The Boeing Company Model 737-300, -400, and -500 series airplanes.
The NPRM published in the Federal Register on February 24, 2015 (80 FR 9667) (''the NPRM''). The
NPRM was prompted by reports of fatigue cracking found at the left-side and right-side upper frame,
at a certain area. The NPRM proposed to require repetitive MFEC inspections for cracking of the left-
side and right-side upper frames, and repair (including open hole HFEC inspections for cracking of
fastener holes) if necessary. The NPRM also provided an optional preventative modification that
would terminate the repetitive inspections at the modified location. We are issuing this AD to detect
and correct fatigue cracking of the upper frame, which can grow in size and result in a severed frame,
leading to rapid decompression and consequent reduced structural integrity of the airplane.
Comments
We gave the public the opportunity to participate in developing this AD. The following presents
the comments received on the NPRM and the FAA's response to each comment.
Requests To Clarify Compliance Time
Europe Airpost and Boeing requested that we revise the NPRM to clarify the ''Condition'' column
of table 1 of paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 737-53A1339, dated
August 12, 2014, which specifies airplanes with certain flight cycles ''on the original issue date of this
service bulletin.'' The commenters questioned whether the corresponding compliance time should be
''on the effective date of the AD.''
For the reasons suggested by both commenters, we agree to add paragraph (i)(3) to this AD to
state that the corresponding reference point is on the effective date of this AD, and we have included
reference to paragraph (i)(3) in all appropriate paragraphs in this AD.
Request for Clarify Inspection Requirements
Boeing requested that we revise paragraph (g) of the proposed AD to address the inspection
requirements in areas of an existing repair to eliminate cracking approved by a Boeing Organization
Designation Authorization (ODA) via FAA Form 8100-9. Boeing explained that this condition is
addressed in note (c) of table 1 of paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin
2
737-53A1339, dated August 12, 2014, and that it effectively terminates the initial and repetitive
inspections required by paragraph (g) of the proposed AD for previously installed frame repairs
approved by the Boeing ODA via FAA Form 8100-9. Boeing requested that the proposed AD address
the terminating action for this repair condition.
We agree that clarification is necessary. Boeing ODA-approved repairs installed prior to the
effective date of this AD are acceptable to terminate the initial and repetitive inspections in the area
under the repair. We have revised paragraph (g) of this AD accordingly, and added a new paragraph
(g)(1) in this AD.
Request To Clarify Required for Compliance (RC) Requirements
Southwest Airlines requested that we clarify paragraph (l)(4) of the proposed AD. Southwest
Airlines explained that note 15 in paragraph 3.A., ''General Information,'' of Boeing Alert Service
Bulletin 737-53A1339, dated August 12, 2014, states that steps in the Work Instructions that are
identified as RC must be accomplished once the actions specified in Boeing Alert Service Bulletin
737-53A1339, dated August 12, 2014, becomes mandated by an AD. Southwest Airlines stated that
note 15 also states that deviations to steps that are not identified as RC do not require approval of an
Alternative Method of Compliance (AMOC). Southwest Airlines stated that paragraph (l)(4) of the
proposed AD specifies that any service information that is identified as RC requires AMOC approval
except as required by paragraph (i)(1) of the proposed AD. Paragraph (k) of the proposed AD states
that the post-repair and post-modification inspections are not mandated by the AD, so it is unclear
whether the proposed AD would require the operator to contact Boeing if there are crack findings
during the post-repair and post-modification inspections, and whether or not the resulting repairs are
subject to the requirements of the AD.
We agree to provide clarification. Paragraph (k) of this AD states that the post-repair and post-
modification inspections specified in tables 4 and 5 of paragraph 1.E., ''Compliance,'' of Boeing Alert
Service Bulletin 737-53A1339, dated August 12, 2014, are not required by this AD (tables 4 and 5
correspond to Parts 6 and 7, respectively, of the service information.). The RC steps in those parts are
also not required by this AD. Any cracking found–whether during accomplishment of the actions
required by an AD or during routine maintenance–is required by 14 CFR 43.13(b) to be repaired
before further flight. However, for clarity, we have revised paragraph (i)(1) of this AD to refer only
to Part 3 and Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1339, dated August 12, 2014. In addition, we have revised paragraph (l)(4) of this AD to refer to
Part 2, Part 3, and Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1339, dated August 12, 2014.
Request To Address Repairs for Damage Other Than Cracking
Southwest Airlines stated that the NPRM does not specifically address existing repairs that
prevent accomplishment of the inspections proposed in paragraph (g) of the proposed AD. Note (c) in
table 1 of paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 737-53A1339, dated
August 12, 2014, specifies that an ODA-approved repair, via FAA Form 8100-9, installed to
eliminate previously found cracking, eliminates the need for the repetitive inspections at the repaired
locations. Southwest requested that we revise the NPRM to apply this provision to repairs for damage
other than cracking. Southwest Airlines also requested that we specifically state that any repair
approved by Boeing via an FAA 8100-9 combined with approval of an AMOC to paragraph (h) of
the proposed AD terminates both the initial and repetitive inspections required by paragraph (g) of
the proposed AD.
We agree to add clarification regarding initial and repetitive inspections. To provide additional
clarification in the rule we have revised the wording in paragraphs (g) and (h) of this AD. Also, we
agree to revise the NPRM to include in this final rule, the provision for repairs for cracking in
paragraph (g)(1) of this AD, and the provision for repairs that were installed for damage other than
3
