Nachrichten für Luftfahrer 2009 Teil II (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung
Maßnahmen:
LTA-Nr.: D-2009-182R2 Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
ersetzt: D-2009-182R1 Airworthiness Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen. Alle
Luftfahrt-Bundesamt erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und
Datum der Bekanntgabe: 17.08.2009 innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle
Muster: AD der ausländischen Behörde: Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen
EASA Emergency AD 2009-0183-E vom 14.08.2009 Zustimmung durch das Luftfahrt-Bundesamt.
AGUSTA / EUROCOPTER / EUROCOPTER
DEUTSCHLAND / SIKORSKY
Fristen:
Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen.
Agusta
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
A109 / AB139 / AW139 EASA Airworthiness Directive.
Eurocopter ------------------------------ DRINGENDE LUFTTÜCHTIGKEITSANWEISUNG ------------------------------
AS332 / AS350 / AS355 / AS365 / SA365 /
EC155 / EC225LP Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA Emergency AD 2009-0183-E vom 14.08.2009
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
Eurocopter Deutschland nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es
EC135 / MBB-BK 117 erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Rechtsbehelfsbelehrung:
Sikorsky Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
S-61N / S-76 / S-92A
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
Geräte-Nr.: Technische Mitteilungen des Herstellers:
3043, 3045, 3048, 3049, 3050, 3051, 3052, Goodrich Service Bulletin 42315-489-01 Revision 1
3056, 3061, Breeze-Eastern Service Bulletin SB BLH-20200-504-25-01
EASA.IM.R.001, EASA.R.002, EASA.R.005, Breeze-Eastern Service Information Letter SIL01 BLH-20200-431
EASA.R.006, EASA.R.008, EASA.R.009, Breeze-Eastern Service Information Letter SIL01 HK-116-5
EASA.R.010, EASA.R.146
Betroffenes Luftfahrtgerät:
AGUSTA / EUROCOPTER / EUROCOPTER DEUTSCHLAND / SIKORSKY
Agusta A109 / AB139 / AW139,
Eurocopter AS332 / AS350 / AS355 / AS365 / SA365 / EC155 / EC225LP,
Eurocopter Deutschland EC135 / MBB-BK 117,
Sikorsky S-61N / S-76 / S-92A
- Baureihen: Alle
- Werk-Nrn.: Alle
-- mit installiertem LIFESAVING SYSTEMS "D-Lok Hook" der Part-Nummer
(P/N) 410-A oder 410-F (die P/N ist Teil der LOT-Nr. 208 oder 1108)
HINWEIS:
Der betroffene Lifesaving Systems "D-Lok Hook" kann an diversen Goodrich Hook Kits,
Goodrich Rescue Hoist Assemblies oder den Breeze-Eastern Rescue Hoist Assemblies
installiert sein.
Betrifft:
(ATA 25) Equipment / Furnishings - D-Lok Hook of the Rescue Hoist - Inspection / Removal from Service /
Replacement
(LTA-Nr.: D-2009-182R1 vom 12.08.2009) Aktenzeichen: (02)T231-502.1/D-2009-182R2 Seite 1 von 2 (LTA-Nr.: D-2009-182R1 vom 12.08.2009) Aktenzeichen: (02)T231-502.1/D-2009-182R2 Seite 2 von 2
EASA AD No.: 2009-0183-E EASA AD No.: 2009-0183-E
EASA EMERGENCY AIRWORTHINESS DIRECTIVE Reason: Field reports from rescue hoist operators have noted surface irregularities and
discontinuities on D-Lok Hooks supplied by Lifesaving Systems with P/N 410-A
and 410-F. It was determined that a non-approved change in the hook
AD No.: 2009-0183-E manufacturing process, from forged material to cast material, is the cause of
the irregularities and discontinuities found in the material.
This condition, if left uncorrected, could lead to the fracture of the hook.
Furthermore, the new manufacturing process has not been shown to be
Date: 14 August 2009
compliant with the applicable regulations.
Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance EASA AD 2009-0124 was issued as an emergency measure to mandate visual
with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States inspection and replacement, as applicable, of D-Lok Hooks supplied by
and of the European third countries that participate in the activities of EASA under Article 66 of
that Regulation. Lifesaving System with P/N 410-A and 410-F and installed on certain Goodrich
Corporation hook kits or rescue hoist assemblies.
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 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 It has been later discovered that the same Lifesaving Systems D-Lok Hooks
an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency P/N are also installed on Breeze-Eastern Corporation rescue hoist assemblies.
[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
EASA AD 2009-0148-E, which superseded EASA AD 2009-0124, required
Type Approval Holders’ Names : Type/Model designations:
inspection of Goodrich and Breeze-Eastern rescue hoist assemblies and, if the
affected D-Lok Hooks were found installed, their removal from service or
Agusta S.p.A, A109 series and AB139/AW139, replacement with serviceable parts.
Eurocopter, AS332, AS350 and AS355 series, EC225,
SA365, AS365 and EC155 series, EASA AD 2009-0179-E, superseding EASA AD 2009-0148-E and keeping its
requirements, reduced the AD applicability and required returning the cast
Eurocopter Deutschland GmbH, EC135 and MBB-BK 117,
hooks to Goodrich or Breeze-Eastern, as applicable, after removal.
Sikorsky Aircraft Corporation S-61, S76 series and S92 helicopters
This AD, which supersedes EASA AD 2009-0179-E keeping its requirements,
TCDS Numbers : EASA R.001, R.002, R.005, R.006, R.008, R.009, R.010 and R.146, extends the AD applicability to Sikorsky S76 series and S92A helicopters.
DGAC France No. 159,
FAA U.S.A. 1H15 and H1NE.
Effective Date: 17 August 2009
Foreign AD : Not applicable
Required Action(s) Required as indicated, unless previously accomplished:
and Compliance
Supersedure : This AD supersedes EASA AD 2009-0179-E dated 11 August 2009 (1) For all helicopters except Sikorsky S76 Series and S92A helicopters:
Time(s):
(1.1) Before the next hoist operation carried out after 11 July 2009 (effective
date of EASA AD 2009-0148-E) inspect the rescue hoist assembly and, if
Equipment / Furnishings – D-Lok Hook of the Rescue Hoist – a Lifesaving Systems D-Lok Hook with P/N 410-A or 410-F and identified
ATA 25 as part of lot number 208 or 1108 (cast hook) is found installed, perform a
Inspection / Removal from Service / Replacement
visual inspection in accordance with the applicable instructions of the
rescue hoist system manufacturer (Goodrich or Breeze-Eastern),
depending on the helicopter type. If the hook does not pass the visual
Manufacturers: Agusta S.p.A., Agusta Aerospace Corporation, American Eurocopter LLC,
inspection, any further operation using the hook is prohibited.
Eurocopter (formerly Eurocopter France), Eurocopter Deutschland GmbH,
The inspections and relevant corrective actions carried out, before 11 July
Eurocopter ESPANA S.A., Sikorsky Aircraft Corporation.
2009 (effective date of EASA AD 2009-0148-E), in accordance with
paragraph (1) or (3) of EASA AD 2009-0124 are acceptable to comply
Applicability: Agusta S.p.A model A109 series and AB139/AW139 helicopters , with paragraph (1.1) of this AD.
and Note: Only the visual inspection criteria of the referenced Goodrich and Breeze-
Eurocopter model AS332, AS350, AS355, SA365, AS365 and EC155 series Eastern publications are applicable. Required Actions and Compliance
and EC225 LP helicopters, Times are as described in this AD section.
and (1.2) After 12 August 2009 (effective date of AD 2009-0179-E) replace the cast
hook with a serviceable part to continue hoist operations and return the
Eurocopter Deutschland GmbH model EC135 and MBB-BK 117 helicopters, removed parts to Goodrich or Breeze-Eastern, as applicable.
and (1.3) After 11 July 2009 (effective date of EASA AD 2009-0148-E), do not
Sikorsky Aircraft Corporation S-61N, S76 series and S92A helicopters, install a D-Lok Hook with P/N 410-A or 410-F and identified as part of lot
number 208 or 1108 on any helicopter.
all serial numbers, if equipped with Lifesaving Systems D-Lok Hooks with part
numbers (P/N) 410-A or 410-F and identified as part of lot number 208 or 1108. (2) For Sikorsky S76 series and S92A helicopters:
Note: the rescue hoist P/N provided in the service information of the rescue (2.1) Before the next hoist operation carried out after the effective date of this
hoist system manufacturers (Goodrich or Breeze-Eastern) is for information AD inspect the rescue hoist assembly and, if a Lifesaving Systems
only. Refer to Lifesaving Systems D-Lok Hooks P/N to determine AD D-Lok Hook with P/N 410-A or 410-F and identified as part of lot number
applicability. 208 or 1108 (cast hook) is found installed, perform a visual inspection in
accordance with the applicable instructions of the rescue hoist system
manufacturer (Goodrich or Breeze-Eastern), depending on the helicopter
type. If the hook does not pass the visual inspection, any further operation
EASA Form 111 Page 1/3 EASA Form 111 Page 2/3
EASA AD No.: 2009-0183-E
using the hook is prohibited.
Lufttüchtigkeitsanweisung
Note: Only the visual inspection criteria of the referenced Goodrich and Breeze-
Eastern publications are applicable. Required Actions and Compliance LTA-Nr.: D-2009-204
Times are as described in this AD section.
Luftfahrt-Bundesamt
(2.2) Within 30 days after the effective date of this AD replace the cast hook Datum der Bekanntgabe: 05.08.2009
with a serviceable part to continue hoist operations and return the
removed parts to Goodrich or Breeze-Eastern, as applicable. Muster: Binder Motorenbau GmbH AD der ausländischen Behörde:
ASH 25 EB 28 EASA AD 2009-0131 vom 23.06.2009
(2.3) After the effective date of this AD, do not install a D-Lok Hook with P/N
410-A or 410-F and identified as part of lot number 208 or 1108 on any Geräte-Nr.: Technische Mitteilungen des Herstellers:
helicopter. 858, EASA.A.076 Binder Motorenbau Technical Note ASH 25 EB 28-B5 vom
17.04.2009
Ref. Publications: Goodrich Service Bulletin 42315-489-01 revision 1,
Breeze-Eastern Corporation Service Information Letter SIL01 BLH-20200-431 Betroffenes Luftfahrtgerät:
original release,
Binder Motorenbau GmbH
Breeze-Eastern Corporation Service Bulletin SB BLH-20200-504-25-01 ASH 25 EB 28
original release,
Breeze-Eastern Corporation Service Information Letter SIL01 HK-116-5 - Baureihen: ASH 25 EB 28
original release.
- Werk-Nrn.: 01 bis 10
Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative
Methods of Compliance for this AD. Betrifft:
Mögliche Loslösung der Querruderscharniere nach einer Landung mit aufgelegtem Flügel im Querruder-
2. The safety assessment has requested not to implement the full consultation
bereich.
process and an immediate publication and notification.
3. Enquiries regarding this AD should be referred to the Airworthiness Maßnahmen:
Directives, Safety Management & Research Section, Certification Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
Directorate, EASA. E-mail: ADs@easa.europa.eu. Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen.
4. For any question concerning the technical content of the requirements in Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
this AD, please contact: vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
Goodrich Corporation , Sensors and Integrated Systems anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
1550 S. Valley Vista Drive, Diamond Bar, California
United States of America Fristen:
Tel: +1 909 569-0210 ; Fax: +1 909 569-0387. Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen.
Goodrich Corporation , Sensors and Integrated Systems Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
Saint-Ouen l'Aumône EASA Airworthiness Directive.
13 Avenue de l'Eguillette BP 7186
Cergy-Pontoise, Val d'Oise 95056 - France Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
Tel: +33 (0) 1 3432 6781 ; Fax: +33 (0) 1 3432 6323. EASA AD 2009-0131 vom 23.06.2009
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
Breeze-Eastern Corporation nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der
700 Liberty Avenue Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Union, New Jersey 07083-8198 USA
Ph.: +1 (908) 686-4000, Ext. 3897, or 3890. Rechtsbehelfsbelehrung:
1-800-929-1919 (Toll-Free US and Canada only) Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
Fax: +1 (908) 688-6495 zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
E-Mail: customerservice@breeze-eastern.com . LTAs werden auch im Internet unter http://www.lba.de publiziert
***
EASA Form 111 Page 3/3 Aktenzeichen: (04)T23-502.1/D-2009-204 Seite 1 von 1
EASA AD No : 2009-0131 EASA AD No : 2009-0131
(2) From the effective date of this AD, after any ground loop, before further flight
EASA AIRWORTHINESS DIRECTIVE inspect the aileron hinges and do all corrective actions as instructed in Binder
Motorenbau TN ASH 25 EB 28-B5, initial issue.
PILOT-OWNER AUTHORISATION
AD No.: 2009-0131
When/Where Part-M applies the inspection requirements of paragraphs (1) and
(2) of this AD, can be done under the scope of the limited pilot-owner
maintenance authorisation.
Date: 23 June 2009
Binder Motorenbau Technical Note (TN) ASH 25 EB 28-B5, initial issue dated
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with
Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and 17 April 2009.
of the European third countries that participate in the activities of EASA under Article 66 of
Ref. Publications:
that Regulation.
The use of later approved revisions of this document is acceptable for
compliance with the requirements of this AD.
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the
continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may Remarks : 1. If requested and appropriately substantiated, EASA can approve
operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness
Directive unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State Alternative Methods of Compliance for this AD.
of Registry [EC 216/2008, Article 14(4) exemption].
2. This AD was posted on 08 May 2009 as PAD 09-064 for consultation
Type Approval Holder’s Name : Type/Model designation(s) : until 05 June 2009. No comments were received during the consultation
period.
Binder Motorenbau GmbH ASH 25 EB 28 Powered-sailplanes 3. Enquiries regarding this AD should be referred to the Airworthiness
Directives, Safety Management & Research Section, Certification
Directorate, EASA. E-mail ADs@easa.europa.eu
TCDS Number : EASA A.076
4. For any questions concerning the technical content of the requirements in
this AD, please contact:
Foreign AD : Not applicable BINDER MOTORENBAU GmbH
Alter Frickenhäuser Weg 15, 97645 Ostheim, GERMANY
Telephone: +49-9777-9200 Facsimile: +49-9777-9201
Supersedure : None E-mail: binder.motorenbau@t-online.de
Flight Controls – Aileron Hinge Bonding Joint –
ATA 27
Inspection / Repair / Reinforcement
Manufacturer(s): Binder Motorenbau GmbH
Applicability: Model ASH 25 EB 28 powered-sailplanes, from serial number 01 to 10
inclusive.
Reason: It has been reported to the manufacturer that the bonding between aileron hinges
and aileron was damaged due to landing with ground loop.
The actions specified by this AD are intended to prevent loss of aileron control
due to undetected damages
Effective Date: 07 July 2009
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) Within 14 days after the effective date of this AD, inspect the aileron hinges
Time(s): in accordance with the accomplishment instructions of Binder Motorenbau
Technical Note (TN) ASH 25 EB 28-B5, initial issue.
(1.1) If any damage is found, before further flight, repair and reinforce the
aileron hinges in accordance with the accomplishment instructions of
Binder Motorenbau TN ASH 25 EB 28-B5, initial issue.
(1.2) If no damage is found, within 6 months after the effective date of this AD
reinforce the aileron hinges in accordance with the accomplishment
instructions of Binder Motorenbau TN ASH 25 EB 28-B5, initial issue.
EASA Form 110 Page 1/2 EASA Form 110 Page 2/2
Blatt Binder Motorenbau Blatt Binder Motorenbau
GmbH GmbH
1 von 4 Technische Mitteilung 2 von 4 Technische Mitteilung
ASH 25 EB 28 – B5 D – 97645 Ostheim ASH 25 EB 28 – B5 D – 97645 Ostheim
Gegenstand: Verstärkung der Querruderscharniere
Binder Motorenbau GmbH
Alter Frickenhäuser Weg 15
97645 Ostheim v.d. Rhön Seite 1 von 2
Betroffen: ASH25 EB 28, EASA TCDS.A.076 - nur Baureihe ASH 25 EB 28 LTB II-A 388 HB DE.21G.0138
Dringlichkeit: Maßnahme 1 innerhalb von 14 Tagen, bzw. bei Landungen mit aufgelegtem Flügel im Prüfprogramm Querruderscharniere
Querruderbereich oder Ringelpietz vor dem nächsten Flug
Maßnahme 2 wenn bei der Inspektion nach Maßnahme 1 Schäden festgestellt werden
Versuch 1:
sofort, ansonsten spätestens bis zum 31.12.2009
Bei jedem Ruderscharnier mit dem Daumen ca. 2 kg Druck auf die Unterseite der Schale ausüben. Dabei darf das
Scharnier nicht nachgeben.
Grund: losgelöste Querruderscharniere nach einer Landung mit
aufgelegtem Flügel im Querruderbereich und Ringelpietz
Die genau Position der Ruderscharniere sind der Zeichnung (Seite 2) zu entnehmen.
Maßnahmen: 1) Prüfen der Verklebung der Querruderscharniere und Messung der Ergebnis: X = Verklebung gelöst / = kein Schaden feststellbar
Torsion der Querruder gemäß Formblatt:
ASH25EB28 Prüfprogramm Querruderscharniere V1.1 V1.2 V1.3 V1.4 V1.5 V1.6 V1.7 V1.8 V1.9
Wenn Schäden vorhanden sind, sind diese sofort beim Hersteller zu reparieren. Querruder
rechts
2) Verstärkung nach Arbeitsanweisung ASH25EB28 vom 02.04.2009 auszuführen Querruder
links
Material und siehe Formblatt ASH25EB28 Prüfprogramm Querruderscharniere
Zeichnungen: und Versuch 2:
Arbeitsanweisung für die Verstärkung der Querruderscharniere
Das Querruder an der Innenseite (siehe Zeichnung) mit einem Unterstellbock festsetzen. An der Außenseite
der ASH25EB28 Werk-Nr. 1-10 vom 02.04.2009
einen Klebeband mit Schlaufe, in der die Zugwaage eingehängt wird anbringen. Zugwaage mit 10 kg quer zie
hen. Die Auslenkung sollte nicht mehr als ca. 7mm haben.
Masse und
Schwerpunktlage: Änderung vernachlässigbar Querruder rechts Querruder links
.
Auslenkung
Hinweise: Die baulichen Änderungen dürfen nur vom Hersteller
Binder Motorenbau GmbH
Alter Frickenhäuser Weg 15 Versuch 3:
97645 Ostheim v.d. Rhön Ansteckflügel abnehmen.
Nun kann die Stirnseite des Querruders in Augenschein genommen werden.
durchgeführt werden.
Kann hier ein Schaden festgestellt werden?
Alle Maßnahmen sind zu prüfen und in den Prüfunterlagen sowie
im Bordbuch freizugeben. ja Beschreibung des Schadens:
-----------------------------------------------------------------------------------------------------
-----------------------------------------------------------------------------------------------------
Ostheim, den 17.04.2009 -----------------------------------------------------------------------------------------------------
Binder Motorenbau
GmbH
nein
(W.Binder)
_________________________________ ______________________________
Diese Technische Mitteilung wurde mit dem Datum vom 23.Juni 2009 durch die EASA unter Ort, Datum Unterschrift
Nummer: EASA AD No.2009-0131 anerkannt:
Blatt Binder Motorenbau Blatt Binder Motorenbau
GmbH GmbH
3 von 4 Technische Mitteilung 4 von 4 Technische Mitteilung
ASH 25 EB 28 – B5 D – 97645 Ostheim ASH 25 EB 28 – B5 D – 97645 Ostheim
Prüfprogramm Seite 2 von 2
EASA AD No.: 2009-0172-E
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2009-205
EASA EMERGENCY AIRWORTHINESS DIRECTIVE
Luftfahrt-Bundesamt AD No.: 2009-0172-E
Datum der Bekanntgabe: 06.08.2009
Muster: EUROCOPTER AD der ausländischen Behörde:
SA 330 F EASA Emergency AD 2009-0172-E vom 05.08.2009
Geräte-Nr.: Technische Mitteilungen des Herstellers: Date: 05 August 2009
3043, EASA.R.002 Eurocopter SA 330 Alert Service Bulletin No. 67.18 vom
03.08.2009 Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance with
Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the
European third countries that participate in the activities of EASA under Article 66 of that Regulation.
Betroffenes Luftfahrtgerät: This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 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
EUROCOPTER aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EC
SA 330 F 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
- Baureihen: SA 330 F, SA 330 G und SA 330 J Type Approval Holder’s Name: Type/Model designation(s):
- Werk-Nrn.: Alle Helikopter dieser Baureihen mit der Hersteller-Modifikation ''Pedal Position
EUROCOPTER SA 330 helicopters
Adjustment System Incorporating Modification'' (MOD) 07.10.304.
Betrifft: TCDS Number: EASA.R.002
Rotor Flight Controls – Flight Crew Pedal Position Adjustment System – Test / Modification
Foreign AD: Not applicable
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA Supersedure: None
Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen.
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt. Rotor Flight Controls – Flight Crew Pedal Position Adjustment
ATA 67
System – Test / Modification
Fristen:
Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
EASA Airworthiness Directive. Manufacturer(s): Sud Aviation, Aérospatiale.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der Model SA 330 F, SA 330 G and SA 330 J helicopters, all serial numbers, if
EASA Emergency AD 2009-0172-E vom 05.08.2009 Applicability: equipped with the pedal position adjustment system incorporating modification
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der (MOD) 07.10.304.
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen. While adjusting the position of the pedal unit on a SA 330 helicopter, the copilot
Rechtsbehelfsbelehrung:
set the position beyond the end limit ("tall pilot" position). This resulted in the
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder separation of the pedal adjustment system and the pedals rocking forward.
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
After investigation, it was determined that the Loctite bond on the "tall pilot" stop
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
nut was damaged, most likely due to aging of the adhesive. The nut came loose
and could no longer perform its stop function. The threaded rod of the adjustment
Reason: system separated from the system.
The separation of the adjustment system, if not corrected, could result in the loss
of control of the pedal units, causing the helicopter to begin rotating.
For the reasons described above, this Emergency AD requires a one-time
functional test and modification (MOD 330A779820.00) of the pedal unit
adjustment system.
Effective Date: 07 August 2009
EASA Form 111 Page 1/2
Aktenzeichen: (02)T23-502.1/D-2009-205 Seite 1 von 1
EASA AD No.: 2009-0172-E
Required as indicated, unless accomplished previously: Lufttüchtigkeitsanweisung
LTA-Nr.: D-2009-206
(1) Within the next 10 flight hours after the effective date of this AD, perform a
functional test of the pedal unit adjustment system in accordance with the
Luftfahrt-Bundesamt
instructions of paragraph 2.B.1 of Eurocopter SA 330 Alert Service Bulletin Datum der Bekanntgabe: 07.08.2009
(ASB) 67.18 (the ASB).
Muster: General Electric AD der ausländischen Behörde:
(2) If any non-conformity is found, before next flight, modify the pedal unit CF6-80 FAA AD 2009-14-08 Amdt. 39-15958
adjustment system in accordance with the instructions of paragraphs 2.B.2,
2.B.3 or 2.B.4 and 2.B.5 of the ASB (MOD 330A779820.00). Geräte-Nr.: Technische Mitteilungen des Herstellers:
Required Action(s) 6318 -keine-
and Compliance
Time(s): (3) If no non-conformity is found, within 3 months after the effective date of this
AD, modify the pedal unit adjustment system in accordance with the Betroffenes Luftfahrtgerät:
instructions of paragraphs 2.B.2, 2.B.3, and 2.B.5 of the ASB (MOD
330A779820.00). General Electric
CF6-80
(4) In case insufficient half-bushings are available when complying with
paragraph (2) or (3) of this AD, flights are authorized without half-bushings - Baureihen: CF6-80C2B5F
for up to 12 months after the effective date of this AD.
- Werk-Nrn.: Alle Triebwerke dieser Baureihe mit ''High-Pressure Compressor Rotor (HPCR)
(5) After the effective date of this AD, do not install a pedal position adjustment Stages 11-14 Spool/Shafts'' mit der Hersteller-Teilenummer (P/N) 1703M74G03.
system on a helicopter, unless it has been modified (MOD 330A779820.00)
in accordance with the requirements of this AD. Betrifft:
Möglicher Bruch von ''High-Pressure Compressor Rotor (HPCR) Stages 11-14 Spool/Shafts'' im Fluge
Eurocopter SA 330 ASB N° 67.18 dated 03 August 2009. aufgrund falsch deklarierter Lebensdauerbegrenzungen.
Ref. Publications: The use of later approved revisions of this document is acceptable for compliance Maßnahmen:
with the requirements of this AD. Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA
Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen.
1. If requested and appropriately substantiated, EASA can approve Alternative Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
Methods of Compliance for this AD. vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
2. The safety assessment has requested not to implement the full consultation anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
process and an immediate publication and notification.
Fristen:
3. Enquiries regarding this AD should be referred to the Airworthiness
Alle anzuwendenden Fristen sind der oben genannten FAA Airworthiness Directive zu entnehmen.
Directives, Safety Management & Research Section, Certification
Remarks: Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
Directorate, EASA; E-mail: ADs@easa.europa.eu.
FAA Airworthiness Directive.
4. For any question concerning the technical content of the requirements in this Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
AD, please contact: FAA AD 2009-14-08 Amdt. 39-15958
EUROCOPTER (STDI), Aéroport de Marseille Provence, Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
13725 Marignane Cedex, France nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der
Telephone: +33 (0) 4 42 85 97 97 - Fax +33 (0) 4 42 85 99 66 Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
E-mail: Directive.technical-support@eurocopter.com
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
EASA Form 111 Page 2/2
Aktenzeichen: (10)T23-502.1/D-2009-206 Seite 1 von 1
[Federal Register: July 1, 2009 (Volume 74, Number 125)] Examining the AD Docket
[Rules and Regulations]
[Page 31350-31351] You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at
From the Federal Register Online via GPO Access [wais.access.gpo.gov] the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
[DOCID:fr01jy09-3] holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Operations office (telephone (800) 647-5527) is
–––––––––––––––––––––––––––––––––– provided in the ADDRESSES section. Comments will be available in the AD docket shortly after
receipt.
DEPARTMENT OF TRANSPORTATION
Comments
Federal Aviation Administration
We provided the public the opportunity to participate in the development of this AD. We have
14 CFR Part 39 considered the comment received. The commenter supports the proposal.
[Docket No. FAA-2009-0121; Directorate Identifier 2008-NE-36-AD; Amendment 39-15958; Conclusion
AD 2009-14-08]
We have carefully reviewed the available data, including the comment received, and determined
RIN 2120-AA64 that air safety and the public interest require adopting the AD as proposed.
Airworthiness Directives; General Electric Company (GE) CF6-80C2B5F Turbofan Engines Costs of Compliance
AGENCY: Federal Aviation Administration (FAA), DOT. We estimate that this AD will affect one engine installed on an airplane of U.S. registry. We also
estimate that the actions would require no work-hours per engine. No parts are required. Based on
ACTION: Final rule. these figures, we estimate there is no cost of this AD to U.S. operators.
–––––––––––––––––––––––––––––––––– Authority for This Rulemaking
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE CF6-80C2B5F Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
turbofan engines. This AD requires removing certain part number (P/N) high-pressure compressor Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
rotor (HPCR) stages 11-14 spool/shafts before they exceed a new, reduced life limit. This AD results Programs, describes in more detail the scope of the Agency's authority.
from an internal GE audit that compared the life limited parts certification documentation to the We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III,
airworthiness limitations section (ALS) of the instructions for continuing airworthiness (ICA). We Section 44701, ''General requirements.'' Under that section, Congress charges the FAA with
are issuing this AD to prevent HPCR stages 11-14 spool/shaft fatigue cracks caused by exceeding the promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
life limit, which could result in a possible uncontained failure of the HPCR spool/shaft and damage to methods, and procedures the Administrator finds necessary for safety in air commerce. This
the airplane. regulation is within the scope of that authority because it addresses an unsafe condition that is likely
to exist or develop on products identified in this rulemaking action.
DATES: This AD becomes effective August 5, 2009.
Regulatory Findings
ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S.
Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room We have determined that this AD will not have federalism implications under Executive Order
W12-140, Washington, DC 20590-0001. 13132. This AD will not have a substantial direct effect on the States, on the relationship between the
national government and the States, or on the distribution of power and responsibilities among the
FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, Engine various levels of government.
Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Part, For the reasons discussed above, I certify that this AD:
Burlington, MA 01803; e-mail: robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238- (1) Is not a ''significant regulatory action'' under Executive Order 12866;
7199. (2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979); and
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a (3) Will not have a significant economic impact, positive or negative, on a substantial number of
proposed AD. The proposed AD applies to GE CF6-80C2B5F turbofan engines. We published the small entities under the criteria of the Regulatory Flexibility Act.
proposed AD in the Federal Register on February 20, 2009 (74 FR 7831). That action proposed to We prepared a summary of the costs to comply with this AD and placed it in the AD Docket.
require removing certain P/N HPCR stages 11-14 spool/shafts before they exceed a new, reduced life You may get a copy of this summary at the address listed under ADDRESSES.
limit.
1 2
List of Subjects in 14 CFR Part 39 AIRWORTHINESS DIRECTIVE
Air transportation, Aircraft, Aviation safety, Safety.
FAA
www.faa.gov/aircraft/safety/alerts/
Aircraft Certification Service
www.gpoaccess.gov/fr/advanced.html
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation 2009-14-08 General Electric Company: Amendment 39-15958. Docket No. FAA-2009-0121;
Administration amends 14 CFR part 39 as follows: Directorate Identifier 2008-NE-36-AD.
PART 39–AIRWORTHINESS DIRECTIVES Effective Date
1. The authority citation for part 39 continues to read as follows: (a) This airworthiness directive (AD) becomes effective August 5, 2009.
Authority: 49 U.S.C. 106(g), 40113, 44701. Affected ADs
§ 39.13 [Amended] (b) None.
2. The FAA amends § 39.13 by adding the following new airworthiness directive: Applicability
(c) This AD applies to General Electric Company (GE) CF6-80C2B5F turbofan engines with a
high-pressure compressor rotor (HPCR) stages 11-14 spool/shaft, part number (P/N) 1703M74G03,
installed. These engines are installed on, but not limited to, Boeing 747 series airplanes.
Unsafe Condition
(d) This AD results from an internal GE audit that compared the life limited parts certification
documentation to the airworthiness limitations section (ALS) of the instructions for continuing
airworthiness (ICA). We are issuing this AD to prevent HPCR stages 11-14 spool/shaft fatigue cracks
caused by exceeding the life limit, which could result in a possible uncontained failure of the HPCR
spool/shaft and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this AD performed within the
compliance times specified unless the actions have already been done.
New Reduced Life Limit for the HPCR Stages 11-14 Spool/Shaft
(f) Remove any CF6-80C2B5F turbofan engine that has an HPCR stages 11-14 spool/shaft, P/N
1703M74G03, before the spool/shaft meets or exceeds the new, reduced life cycle limit of 19,500
cycles.
Installation Prohibition
(g) After the effective date of this AD, do not install any CF6-80C2B5F turbofan engine that has
an HPCR stages 11-14 spool/shaft, P/N 1703M74G03, that meets or exceeds 19,500 cycles.
Alternative Methods of Compliance
(h) The Manager, Engine Certification Office, has the authority to approve alternative methods
of compliance for this AD if requested using the procedures found in 14 CFR 39.19.
3 4
