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
2018-06-10 Honda Aircraft Company LLC: Amendment 39-19230; Docket No. FAA-2018-0223;
Product Identifier 2018-CE-007-AD.
(a) Effective Date
This AD is effective April 13, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Honda Aircraft Company LLC Model HA-420 airplanes, serial numbers
42000011 through 4200089, that:
(1) have power brake valve, part number (P/N) HJ1-13243-101-005 or HJ1-13243-101-007,
installed; and
(2) are certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code
32, Landing Gear.
(e) Unsafe Condition
This AD was prompted by reports of unannunciated asymmetric braking during ground
operations and landing deceleration. We are issuing this AD to detect failure of the power brake
valve. The unsafe condition, if not addressed, could result in degraded braking performance and
reduced directional control during ground operations and landing deceleration.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Insert Temporary Revision into the Airplane Flight Manual (AFM)
Before further flight after April 13, 2018 (the effective date of this AD) insert Honda Aircraft
Company Temporary Revision TR 01.1, dated February 16, 2018, into the Honda Aircraft Company
(Honda) HA-420 Airplane Flight Manual (AFM) (the temporary revision). This insertion and the
steps therein may be performed by the owner/operator (pilot) holding at least a private pilot
certificate and must be entered into the airplane records showing compliance with this AD in
accordance with 14 CFR 43.9 (a)(1)-(4) and 14 CFR 91.417(a)(2)(v). The record must be maintained
as required by 14 CFR 91.417, 121.380, or 135.439.
6
(h) Replace the Power Brake Valve (PBV)
As of and any time after the effective date of this AD, if the PBV fails any of the pilot checks
specified in the temporary revision, before further flight, replace the PBV, P/N HJ1-13243-101-005
or P/N HJ1-13243-101-007, with the improved design PBV, P/N HJ1-13243-101-009. Do the
replacement using the Accomplishment Instructions in Honda Service Bulletin SB-420-32-001, dated
January 8, 2018. Before further flight after installing P/N HJ1-13243-101-009, remove the temporary
revision from the Honda HA-420 AFM.
(i) Optional Terminating Action for Inserting the AFM Temporary Revision/Pilot Checks
(1) Instead of inserting the temporary revision or at any time after inserting the temporary
revision required by paragraph (g) of this AD, you may replace the installed PBV, P/N HJ1-13243-
101-005 or P/N HJ1-13243-101-007, with the improved design PBV, P/N HJ1-13243-101-009. The
replacement must be done using the Accomplishment Instructions in Honda Service Bulletin SB-420-
32-001, dated January 8, 2018. Before further flight after installing P/N HJ1-13243-101-009, remove
the temporary revision from the Honda HA-420 AFM.
(2) If you choose to follow the temporary revision required by paragraph (g) of this AD instead
of the optional replacement in paragraph (i)(1) of this AD, the on-condition replacement required by
paragraph (h) of this AD is still required before further flight.
(j) No Reporting Requirement
Although Honda Service Bulletin SB-420-32-001, dated January 8, 2018, specifies to submit
certain information to the manufacturer, this AD does not require that action.
(k) Special Flight Permit
Special flight permits for this AD are prohibited.
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Atlanta 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 (m) 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.
(3) For service information that contains steps that are labeled as Required for Compliance (RC),
the provisions of paragraphs (h) and (i) 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 this AD. 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.
7
(m) Related Information
For more information about this AD, contact Samuel Kovitch, Aerospace Engineer, Atlanta
ACO Branch, FAA, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474-5570;
fax: (404) 474-5605; email: samuel.kovitch@faa.gov.
(n) 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. 510(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD,
unless this AD specifies otherwise.
(i) Honda Aircraft Company Temporary Revision TR 01.1, dated February 16, 2018, to the
Honda Aircraft Company HA-420 Airplane Flight Manual.
(ii) Honda Aircraft Company Service Bulletin SB-420-32-001, dated January 8, 2018.
(3) For Honda Aircraft Company LLC service information identified in this AD, contact Honda
Aircraft Company LLC, 6430 Ballinger Road, Greensboro, North Carolina 27410; telephone (336)
662-0246; internet: http://www.hondajet.com.
(4) You may view this service information at the FAA, Policy and Innovation Division, 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 the 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 March 19, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division,
Aircraft Certification Service.
8
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2018-090 38144 Braunschweig
EASA AD 2018-0067 vom 23.03.2018 Fax: +49-531-2355-5298
email: ad@LBA.de
ENSTROM 05.04.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: Enstrom Helicopter Corporation
Hersteller: Enstrom Helicopter Corporation
Muster: ENSTROM F-28 / 480
Baureihen: F-28A, F-28C, F-28C-2, F-28F, F-28F-R, 280, 280F, 280FX, 480 und 480B
Werknummern: Alle
Gerätenummer: 3041, EASA.IM.R.122, FAA TCDS H1CE
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2018-0067 vom 23.03.2018
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 2018-090 geführt.
Betrifft:
(ATA 62) Main Rotor - Hydraulic Damper / Belt Tension Shaft Rod End Assembly - Inspection
Hinweis: Die in der EASA AD 2018-0067 aufgeführte FAA AD 2017-26-03 wird beim Luftfahrt-Bundesamt unter der
LTA-Nr. D-2017-305 geführt.
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 2018-0067 vom 23.03.2018 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-2018-090 Seite 1 von 1 165/2018
EASA AD No.: 2018-0067
Airworthiness Directive
AD No.: 2018-0067
Issued: 23 March 2018
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):
ENSTROM HELICOPTER CORPORATION F-28, 280 and 480 helicopters
Effective Date: 06 April 2018
TCDS Number(s): EASA.IM.R.122
Foreign AD: Federal Aviation Administration (FAA) AD 2017-26-03 dated 20 December 2017.
Supersedure: None
ATA 62 – Main Rotor – Hydraulic Damper / Belt Tension Shaft Rod End Assembly –
Inspection
Manufacturer(s):
Enstrom Helicopter Corporation (EHC)
Applicability:
F-28A, F-28C, F-28C-2, F-28F, F-28F-R, 280, 280F, 280FX, 480 and 480B helicopters, all variants, all
serial numbers (s/n).
Note 1: FAA AD 2017-26-03 applies to additional helicopter models but, at this time, these are not
validated in Europe.
Definitions:
For the purpose of this AD, the following definitions apply:
The applicable SDB: EHC Service Directive Bulletin (SDB) 0127 Revision 1, dated 06 October 2017,
and SDB T-058 original issue, dated 02 August 2017, as applicable to helicopter model.
Affected Part: Main rotor hydraulic damper and belt tension shaft rod end bearing assemblies,
Part Number (P/N) 01-824-08E-011, P/N 09455-01-824-08E-011, P/N ECD091-1, P/N ASMK8T,
P/N M81935/1-08K, P/N MS21242S8K and P/N MTK8.
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EASA AD No.: 2018-0067
Groups: Group 1 helicopters are those that have an affected part installed. Group 2 helicopters are
those that do not have an affected part installed.
Reason:
An occurrence was reported of a failed rod end bearing assembly of one of the hydraulic damper
assemblies of the main rotor system. Analysis of the rod end revealed corrosion in the root of the
threads.
This condition, if not detected and corrected, could lead to cracks in a bearing assembly, possibly
resulting in failure of the rod end, loss of a main rotor blade and consequent loss of control of the
helicopter.
Prompted by these findings, EHC issued the applicable SDB. Multiple supplier P/N rod end bearing
assemblies are eligible for installation. Consequently, the FAA, the State of Design authority for the
affected helicopter type, issued AD 2017-26-03, which was adopted by EASA, applicable to
helicopters that have an affected part installed. That AD requires a one-time inspection of the
affected part(s), and, if corrosion is found, replacement of the affected part.
The FAA AD does not require repetitive inspections, whereas the applicable SDB specifies to repeat
the inspection every 100 flight hours (FH) or during an annual inspection. EASA has determined that
these inspections are necessary to ensure the continued airworthiness of the affected helicopters. It
is expected that the FAA will take further AD action to require these repetitive inspections, but
EASA has no information on when that AD will be issued.
For the reasons described above, this AD requires repetitive inspections of the affected parts to
detect corrosion and, depending on findings, replacement.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Repetitive Inspection(s):
(1) For Group 1 helicopters: Within 100 FH or during the next scheduled annual inspection,
whichever occurs first after the inspection as required by FAA AD 2017-26-03 (as adopted by
EASA), and, thereafter, at intervals not to exceed 100 FH, or during each scheduled annual
inspection, whichever occurs first, inspect each affected part in accordance with the
instructions of the applicable SDB.
Corrective Action(s):
(2) If, during any inspection as required by paragraph (1) of this AD, corrosion is detected, before
next flight, replace the affected part with a serviceable part in accordance with the instructions
of the applicable SDB.
Reporting:
(3) Within 30 days after each inspection, as required by paragraph (1) of this AD, report the
inspection results (including no findings) to Enstrom Product Support in accordance with the
instructions of the applicable SDB.
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EASA AD No.: 2018-0067
Parts Installation:
(4) For Group 1 and Group 2 helicopters: From the effective date of this AD, it is allowed to install
an affected part on any helicopter, provided the part is new, or has passed an inspection (no
corrosion detected) in accordance with the instructions of the applicable SDB, and that,
following installation, the part is inspected as required by paragraph (1) of this AD.
Terminating Action(s):
(5) None.
Ref. Publications:
Enstrom Helicopter Corporation SDB 0127 Revision 1 dated 06 October 2017.
Enstrom Helicopter Corporation SDB T-058 dated 02 August 2017.
Remarks:
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of
Compliance for this AD.
2. This AD was posted on 22 December 2017 as PAD 17-177 for consultation until 19 January
2018. 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: Enstrom Helicopter Corporation, 2209 22nd Street, Menominee, Michigan 49858,
United States of America, Telephone: +1 906-863-1200, Fax: +1 906-863-6621,
E-mail: engineering@enstromhelicopter.com.
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An agency of the European Union
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2018-091 38144 Braunschweig
EASA AD 2018-0075 vom 05.04.2018 Fax: +49-531-2355-5298
email: ad@LBA.de
GE AVIATION CZECH 06.04.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: GE Aviation Czech s.r.o.
Hersteller: GE Aviation Czech s.r.o. (vormals Walter Engines a.s.)
Muster: M601/H80
Baureihen: H80-200
Werknummern: Alle
Betroffen sind Triebwerke, die in Kombination mit Avia Propeller AV-725
Propellern in Aircraft Industries (AI, vormals LET) L 410 UVP-E20 und L 410
UVP-E20 CARGO Flugzeugen installiert sind.
Gerätenummer: EASA.E.070
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2018-0075 vom 05.04.2018
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 2018-091 geführt.
Betrifft:
(ATA 72) Engines - Beta Switch - 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 2018-0075 vom 05.04.2018 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-2018-091 Seite 1 von 1 181/2018
EASA AD No.: 2018-0075
Airworthiness Directive
AD No.: 2018-0075
Issued: 05 April 2018
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):
GE AVIATION CZECH H80-200 engines
Effective Date: 19 April 2018
TCDS Number(s): EASA.E.070
Foreign AD: Not applicable
Supersedure: None
ATA 72 – Engines – Beta Switch – Replacement
Manufacturer(s):
GE Aviation Czech s.r.o. (formerly Walter Engines a.s.)
Applicability:
H80-200 engines, in combination with Avia Propeller AV-725 propellers, installed on Aircraft
Industries (AI, formerly LET) L 410 UVP-E20 and L 410 UVP-E20 CARGO aeroplanes.
Definitions:
For the purpose of this AD, the following definitions apply:
The SB: GE Aviation Czech Service Bulletin (SB) SB-H80-76-00-00-0036 Revision 02.
Groups: Group 1 engines are equipped with a Beta switch Part Number (P/N) P-S-2. Group 2
engines are those not equipped with a Beta switch P/N P-S-2.
Reason:
A fatal accident of an L 410 UVP-E20 aeroplane has been reported. Preliminary investigation
determined that there was an annunciation of Beta mode on right hand engine, that the propeller
went inadvertently behind the fine pitch position and reached a negative thrust position, and that
the pitch lock system did not intervene.
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EASA AD No.: 2018-0075
This event occurred on approach at a speed and altitude which did not allow the crew to recover
this control system malfunction.
This condition, if not corrected, could lead to reduced control or loss of control of the aeroplane.
To address this unsafe condition, GE Aviation Czech issued the SB, providing modification
instructions.
For the reason described above, this AD requires modification of the engine. Addressing the same
unsafe condition at aeroplane level, EASA also issued AD 2018-0057, requiring modification of
affected AI L 410 UVP-E20 and L 410 UVP-E20 CARGO aeroplanes, if equipped with GE Aviation
H80-200 engines and Avia Propeller AV 725 propellers.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Modification/Inspection(s):
(1) For Group 1 engines: Within 25 flight hours, 20 flight cycles, or 30 days, whichever occurs first
after the effective date of this AD, inspect and adjust the engine push-pull control P/N
M601-76.3, and replace Beta switch P/N P-S-2 with a Beta switch P/N P-S-2A, in accordance
with the instructions of the SB.
Corrective Action(s):
(2) If, during the inspection as required by paragraph (1) of this AD, any deficiencies are detected,
before next flight, accomplish the applicable corrective action(s) in accordance with the
instructions of the SB.
Parts Installation:
(3) Do not install a Beta switch P/N P-S-2 on an engine, as required by paragraph (3.1) or (3.2) of
this AD, as applicable.
(3.1) For Group 1 engines: After modification of the engine as required by paragraph (1) of this
AD.
(3.2) For Group 2 engines: From the effective date of this AD.
(4) From the effective date of this AD, it is allowed to install on any AI L 410 UVP-E20 or
L 410 UVP-E20 CARGO aeroplane an H80-200 engine, provided it is not a Group 1 engine (see
Note 1 of this AD).
Note 1: For the purpose of this AD, removal of an engine from an aeroplane and subsequent
re-installation of that engine on that same aeroplane within the same aeroplane maintenance visit
does not constitute “installation” as specified in paragraph (4) of this AD.
Ref. Publications:
GE Aviation Czech SB-H80-76-00-00-0036 Revision 02 dated 29 March 2018.
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