Nachrichten für Luftfahrer 2016 Teil 2 (weicht ggf. von Druckversion ab)
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 adding the following new airworthiness directive (AD):
5
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2016-08-18 Piper Aircraft, Inc.: Amendment 39-18495; Docket No. FAA-2014-0338; Directorate
Identifier 2014-CE-010-AD.
(a) Effective Date
This AD is effective June 6, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Piper Aircraft, Inc. Model PA-31-350 airplanes, serial numbers 31-5001
through 31-5004, 31-7305005 through 31-8452024, and 31-8253001 through 31-8553002,
certificated in any category, that are equipped with the following engines and fuel pump hose
assemblies:
Table 1 to Paragraph (c) of This AD–Applicable Engines and Fuel Pump Hose Assemblies
Engine Manufacturer's hose Manufacturer's part Hose description
name number (P/N)
TIO-540-J2B Hose Assembly—Fuel Piper 39995-034 Inlet fuel hose to engine
(right wing) fuel pump.
LTIO-540-J2B Hose, Fuel pump to Lycoming LW-12877- Exit fuel hose from engine
(left wing) Injector 6S142 fuel pump.
TIO540-J2BD Hose, Fuel pump to Lycoming LW-12877- Exit fuel hose from engine
(right wing) Injector 6S142 fuel pump.
LTIO-540-J2BD Hose Assembly—Fuel Piper 39995-034 Inlet fuel hose to engine
(left wing) fuel pump.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code
73: Engine Fuel and Control.
(e) Unsafe Condition
This AD was prompted by a report of an engine fire caused by a leak in the fuel pump inlet hose.
We are issuing this AD to correct the unsafe condition on these products.
6
(f) Compliance
Comply with this AD within the compliance times specified in paragraphs (g)(1) through (j)(2)
of this AD, unless already done.
(g) Ensure Proper Clearance Between the Fuel Hose Assembly and the Turbocharger Support
Assembly
(1) Within the next 60 hours time-in-service (TIS) after June 6, 2016 (the effective date of this
AD) or within the next 6 months after June 6, 2016 (the effective date of this AD), whichever occurs
first, inspect to determine the clearance between the inlet and exit fuel hose assemblies listed in table
1 to paragraph (c) of this AD, and each turbocharger support assembly, Lycoming P/N LW-18302.
There should be a minimum 3/16-inch clearance. Do the inspection following the INSTRUCTIONS
section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(2) Before further flight after the inspection required in paragraph (g)(1) of this AD, if the
measured clearance is less than 3/16-inch, make all necessary adjustments to make the clearance a
minimum of 3/16-inch between the inlet and exit fuel hose assemblies listed in table 1 to paragraph
(c) of this AD and each turbocharger support assembly, Lycoming P/N LW-18302, following the
INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(h) Visually Inspect the Fuel Hose Assembly and Replace if Necessary
(1) Within the next 60 hours TIS after June 6, 2016 (the effective date of this AD) or within the
next 6 months after June 6, 2016 (the effective date of this AD), whichever occurs first, visually
inspect the inlet and exit fuel hose assemblies listed in table 1 to paragraph (c) of this AD for
evidence of leaking, cracking, chafing, and any other sign of damage. Do the inspection following the
INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(2) Before further flight after the inspection required in paragraph (h)(1) of this AD, if any
evidence of leaking, cracking, chafing, or any other sign of damage is found in any inlet or exit fuel
host assembly listed in table 1 to paragraph (c) of this AD, replace the fuel hose assembly with a
serviceable part. Do the replacement following the INSTRUCTIONS section of Piper Aircraft, Inc.
Service Bulletin No. 1257A, dated August 4, 2015.
(i) Visually Inspect the Turbocharger Support Assembly and Replace if Necessary
(1) Within the next 60 hours TIS after June 6, 2016 (the effective date of this AD) or within the
next 6 months after June 6, 2016 (the effective date of this AD), whichever occurs first, visually
inspect each turbocharger support assembly, Lycoming P/N LW-18302, for evidence of chafing and
any other signs of damage. Do the inspection following the INSTRUCTIONS section of Piper
Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(2) Before further flight after the inspection required in paragraph (i)(1) of this AD, if any
evidence of chafing or any other sign of damage is found on any turbocharger support assembly,
replace Lycoming P/N LW-18302 with a serviceable part. Do the replacement following the
INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(j) Engine Run-Up
(1) If any fuel line component was adjusted or replaced during any actions required in
paragraphs (g)(1) through (i)(2) of this AD, before further flight, perform an engine run-up on the
ground to check for leaks. Do the engine run-up following the INSTRUCTIONS section of Piper
Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
7
(2) If any leaks found during the engine run-up required in paragraph (j)(1) of this AD emanate
from any fuel line component adjusted, repaired, or replaced during any actions required in
paragraphs (g)(1) through (i)(2) of this AD, before further flight, take all necessary corrective actions
following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated
August 4, 2015.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Atlanta 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 the Related Information section of this AD.
(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.
(l) Related Information
For more information about this AD, contact Gary Wechsler, Aerospace Engineer, FAA, Atlanta
ACO, 1701 Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474-5575; fax: (404)
474-5606; email: gary.wechsler@faa.gov.
(m) 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.
(i) Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(ii) Reserved.
(3) For Piper Aircraft, Inc. service information identified in this AD, contact Piper Aircraft, Inc.,
926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567-4361; fax: (772) 978-6573;
Internet: www.piper.com/home/pages/Publications.cfm.
(4) You may view this service information at FAA, Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call
(816) 329-4148.
(5) 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 Kansas City, Missouri, on April 14, 2016.
Robert P. Busto,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
8
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2016-142 38144 Braunschweig
EASA AD 2016-0098 vom 23.05.2016 Fax: +49-531-2355-5298
email: ad@LBA.de
TURBOMECA 31.05.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: TURBOMECA
Hersteller: Turbomeca
Muster: ARRIEL 2
Baureihen: ARRIEL 2B
Werknummern: Alle
Die betroffenen Triebwerke sind in Airbus Helicopters (früher Eurocopter) AS
350 B3 Hubschraubern installiert, aber nicht auf diese beschränkt.
Gerätenummer: 7003, EASA.E.001
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2016-0098 vom 23.05.2016
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 2016-142 geführt.
Betrifft:
(ATA 73) Engine Fuel & Control - Hydro-Mechanical Metering Unit - Modification
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 2016-0098 vom 23.05.2016 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-2016-142 Seite 1 von 1 237/2016
EASA AD No.: 2016-0098
Airworthiness Directive
AD No.: 2016-0098
Issued: 23 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):
TURBOMECA ARRIEL 2 engines
Effective Date: 06 June 2016
TCDS Number(s): EASA E.001
Foreign AD: Not applicable
Supersedure: None
ATA 73 – Engine Fuel & Control – Hydro-Mechanical Metering Unit – Modification
Manufacturer(s):
Turbomeca
Applicability:
ARRIEL 2B engines, all serial numbers.
These engines are known to be installed on, but not limited to, Airbus Helicopters (formerly
Eurocopter) AS 350 B3 helicopters.
Reason:
Following a report of an un-commanded in-flight shut-down (IFSD), Turbomeca carried out an
engineering investigation. This investigation concluded that the cause of the event was a low
returning spring rate of the needle of the hydro-mechanical metering unit (HMU), which enabled
needle oscillation during rapid engine deceleration.
This condition, if not corrected, could lead to further cases of IFSD, possibly resulting in an
emergency landing on single engine.
To address this potential unsafe condition, Turbomeca developed modification (Mod) TU 158, which
increases needle return spring rate to prevent oscillation during rapid deceleration, thus preventing
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 2
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EASA AD No.: 2016-0098
the risk of un-commanded IFSD. Turbomeca also published Mandatory Service Bulletin (MSB) 292
73 3158 for embodiment of this modification in service.
For the reasons described above, this AD requires modification of the engine to embody Mod TU
158.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
(1) For an engine in pre-Mod TU 158 configuration, within 200 engine hours, or within 5 months,
whichever occurs first after the effective date of this AD, modify the engine by replacing the
HMU with a serviceable HMU (see Note of this AD) in accordance with the instructions of
Turbomeca MSB 292 73 3158 version A.
Note: For the purpose of this AD, a serviceable HMU is one that embodies Mod TU 158.
(2) After modification of an engine as required by paragraph (1) of this AD, it is allowed to install a
replacement HMU on that engine, provided the HMU is a serviceable one (see Note of this AD).
(3) For an engine in post-Mod TU 158 configuration, from the effective date of this AD, it is allowed
to install an HMU on the engine provided the replacement HMU is serviceable (see Note of this
AD).
Ref. Publications:
Turbomeca MSB 292 73 3158 version A dated 07 April 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 19 April 2016 as PAD 16-056 for consultation until 17 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: Turboméca S.A., ARRIEL 2 Customer Support, 40220 Tarnos, France
Fax: +33 5 59 74 45 15, or your usual or nearest TURBOMECA technical representative (refer to
http://www.turbomeca-support.com).
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 2
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An agency of the European Union
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2016-143 38144 Braunschweig
EASA AD 2016-0099 (Correction: 25.05.2016) Fax: +49-531-2355-5298
vom 24.05.2016 email: ad@LBA.de
PZL-SWIDNIK 31.05.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: Wytwornia Sprzetu Komunikacyjnego "PZL-Swidnik" S.A.
Hersteller: Wytwornia Sprzetu Komunikacyjnego "PZL-Swidnik" S.A.
Muster: PZL SW-4
Baureihen: PZL SW-4
Werknummern: Alle
Gerätenummer: EASA.R.100
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2016-0099 (Correction: 25.05.2016) 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 2016-143 geführt.
Betrifft:
(ATA 64) Tail Rotor - Tail Rotor Blades - 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 2016-0099 (Correction: 25.05.2016) 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-2016-143 Seite 1 von 1 239/2016
EASA AD No.: 2016-0099
Airworthiness Directive
AD No.: 2016-0099
[Correction: 25 May 2016]
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):
WSK „PZL-ŚWIDNIK” S.A. PZL SW-4 helicopters
Effective Date: 07 June 2016
TCDS Number(s): EASA.R.100
Foreign AD: Not applicable
Supersedure: None
ATA 64 – Tail Rotor – Tail Rotor Blades – Inspection / Replacement
Manufacturer(s):
Wytwórnia Sprzętu Komunikacyjnego (WSK) “PZL-Świdnik” Spółka Akcyjna (S.A.)
Applicability:
PZL SW-4 helicopters, all serial numbers (S/N).
Reason:
During an inspection of attachment components of the tail rotor (TR) blades, Part Number (P/N)
60.02.680.00.01, installed on a military SW-4 helicopter, traces of corrosion were found inside the
feathering hinge case P/N 60.02.686.01.01, which is an integral part of the TR blade. The blade had
accumulated 671 flight hours (FH) during a 91 months service period. Additional non-destructive
and destructive inspections and tests of the TR blade, accomplished during the investigation to
detect the scope of corrosive damage, revealed dark irregular corrosion stains and pits on the
internal surface of feathering hinge case in the vicinity of the hole, through which passes the pin
attaching the blade to the hub tension-torsion strap. No cracks of the feathering hinge case were
detected.
The application of insufficient anticorrosion protective coating was identified as a probable cause of
the corrosion inside the feathering hinge case. The corrosion promoting conditions are: moisture
collected inside the case and possible defects of the case internal surface, caused by the tension-
torsion strap. The anticorrosion protective coating can be damaged also during installation and/or
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 4
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EASA AD No.: 2016-0099
removal of a TR blade. TR blade feathering hinge case surface damage, due to corrosion, affects the
fatigue strength of that part and can lead to fatigue cracking.
This condition, if not detected and corrected, could lead to structural failure of the TR and
consequent loss of the TR anti-torque function, possibly resulting in loss of control of the helicopter.
To address this unsafe condition, WSK "PZL-Świdnik" S.A. issued Mandatory Bulletin (MB) No.
BO-60-16-77 providing instructions for inspection and, depending on findings, application of anti-
corrosion protection inside the TR feathering hinge case.
For the reasons described above, this AD requires replacement of affected TR blades, repetitive
inspections of each TR blade feathering hinge case to detect corrosion and to determine the
condition of the anti-corrosion protective coating and, depending on findings, replacement of
affected TR blades. This AD allows installation of TR blade in conformity with an identified design
standard.
This AD is republished to correct service information reference in Table 1 of this AD.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
For all helicopters equipped with TR blades P/N 60.02.680.00.01, except blades having serial
number (S/N) A.60.04.027, S/N A.60.04.28, and S/N A.60.05.064 or higher:
(1) Before exceeding 400 FH accumulated by a TR blade since new (see Note 1 of this AD) or within
12 months after the effective date of this AD, whichever occurs first, replace each 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).
Note 1: To obtain TR blade manufacturing date, contact WSK "PZL-Świdnik" S.A., as applicable.
For all helicopters equipped with TR blade P/N 60.02.680.00.01:
(2) Within the compliance time defined in Table 1 of this AD, as applicable, and, thereafter, at
intervals not to exceed 36 months accumulated by the TR blade since the previous inspection
or repair (see Note 2 of this AD), as applicable, inspect each TR blade in accordance with the
instructions of Attachment 1 of WSK "PZL-Świdnik" S.A. MB No. BO-60-16-77.
Note 2: For the purpose of the paragraph (2) of this AD, a “repair” is a maintenance action
accomplished by WSK "PZL-Świdnik" S.A. in accordance with the instructions of Chapter II
paragraph 4. of WSK "PZL-Świdnik" S.A. MB No. BO-60-16-77.
TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 4
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