Nachrichten für Luftfahrer 2009 Teil II (weicht ggf. von Druckversion ab)
15,000 total flight hours, or within 18 months after the issuance of the original airworthiness Alternative Methods of Compliance (AMOCs)
certificate or original export certificate of airworthiness, whichever occurs later.
(m)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Kelly
Lubrication McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle ACO,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6490; fax (425) 917-
(i) Within the compliance times specified in paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of this AD, 6590; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14
as applicable: Lubricate the ballnut and ballscrew in accordance with Part 3 of the Accomplishment CFR 39.19.
Instructions of Boeing Service Bulletin 777-27A0059, Revision 2, dated January 15, 2009. Repeat the (2) To request a different method of compliance or a different compliance time for this AD,
lubrication thereafter at intervals not to exceed 2,000 flight hours or 12 months, whichever occurs follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which
first. the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards
(1) For airplanes identified in paragraph (f)(1) of this AD: Before the accumulation of 15,000 District Office (FSDO), or lacking a PI, your local FSDO.
total flight hours, or within 18 months after the effective date of this AD, whichever occurs later.
(2) For airplanes identified in paragraph (f)(2) or (f)(4) of this AD: Before the accumulation of Material Incorporated by Reference
15,000 flight hours since the replacement of the HSTA, or within 18 months after the effective date
of this AD, whichever occurs later. (n) You must use Boeing Service Bulletin 777-27A0059, Revision 2, dated January 15, 2009, to
(3) For airplanes identified in paragraph (f)(3) of this AD: Before the accumulation of 3,500 do the actions required by this AD, unless the AD specifies otherwise.
flight hours since the replacement of the HSTA, or within 12 months after the effective date of this (1) The Director of the Federal Register approved the incorporation by reference of this service
AD, whichever occurs later. information under 5 U.S.C. 552(a) and 1 CFR part 51.
(4) For airplanes that have received an original airworthiness certificate or original export (2) For service information identified in this AD, contact Boeing Commercial Airplanes,
certificate of airworthiness on or after the effective date of this AD: Before the accumulation of Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-
15,000 total flight hours, or within 18 months after the issuance of the original airworthiness 2207; telephone 206-544-5000, extension 1, fax 206-766-5680; e-mail me.boecom@boeing.com;
certificate or original export certificate of airworthiness, whichever occurs later. Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information at the FAA, Transport Airplane
Credit for Actions Accomplished According to Earlier Issues of the Service Bulletin Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this
material at the FAA, call 425-227-1221 or 425-227-1152.
(j) Actions performed prior to the effective date of this AD, in accordance with Boeing Alert (4) You may also review copies of the service information that is incorporated by reference at the
Service Bulletin 777-27A0059, dated September 18, 2003; or Boeing Alert Service Bulletin 777- National Archives and Records Administration (NARA). For information on the availability of this
27A0059, Revision 1, dated August 18, 2005; are considered acceptable for compliance with the material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_
corresponding actions specified in paragraphs (g), (h), and (i) of this AD. federal_regulations/ibr_locations.html.
Credit for Hard-Time Replacement of HSTA Issued in Renton, WA, on June 24, 2009.
Ali Bahrami,
(k) Any HSTA overhauled within the compliance times specified in paragraphs (g), (h), and (i) Manager, Transport Airplane Directorate,
of this AD or before the effective date of this AD–as part of a ''hard-time'' replacement program that Aircraft Certification Service.
includes removal of the HSTA from the airplane and overhaul of the stabilizer ballscrew in
accordance with original equipment manufacturer component maintenance manual instructions–
meets the intent of one detailed inspection, one freeplay inspection, and one lubrication of the HSTA.
Therefore, any such HSTA is considered acceptable for compliance with the initial accomplishment
of the actions specified in paragraphs (g), (h), and (i) of this AD, and repetitions of those actions may
be determined from the performance date of that overhaul.
Parts Installation
(l) As of the effective date of this AD, no person may install, on any airplane, a horizontal
stabilizer trim actuator that is not in a ''known serviceable condition'' as defined in Note 6, section
3.A., of Boeing Alert Service Bulletin 777-27A0059, Revision 2, dated January 15, 2009; unless a
detailed inspection, freeplay measurement, and lubrication of that actuator are performed in
accordance with paragraphs (g), (h), and (i) of this AD, as applicable.
7 8
EASA AD No.: 2008-0025R1
Lufttüchtigkeitsanweisung EASA AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2008-084R1
ersetzt: D-2008-084 AD No.: 2008-0025R1
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 07.08.2009
Muster: ROLLS-ROYCE TURBOMECA AD der ausländischen Behörde:
RTM 322-01/9 EASA AD 2008-0025R1 vom 06.07.2009
Date: 06 July 2009
Geräte-Nr.: Technische Mitteilungen des Herstellers:
EASA.E.009 Rolls-Royce Turbomeca Ltd Alert Service Bulletin SBP-M3-A-04- Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with
40-00-01A-A-A 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
ROLLS-ROYCE TURBOMECA 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 of Registry
RTM 322-01/9 [EC 216/2008, Article 14(4) exemption].
- Baureihen: RTM322-01/9 Type Approval Holder’s Name : Type/Model designation(s) :
- Werk-Nrn.: Alle Triebwerke dieser Baureihe ohne die Hersteller-Modifikation C3003. ROLLS-ROYCE TURBOMECA Ltd RTM322-01/9 turboshaft engines
Betrifft:
TCDS Number : EASA.E.009
Möglicher Triebwerksausfall im Fluge durch Bruch von Turbinenschaufeln der 2. Stufe Hochdruckturbine
aufgrund von ungünstigen Betriebsbedingungen, die unter niedrigen Temperaturen und geringen Flughöhen
auftreten können. Foreign AD : Not applicable
Maßnahmen: Revision : This AD revises EASA AD 2008-0025, dated 12 February 2008
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
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 vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchge- Life Limits / Critical Parts - Special Regular Inspections after
führt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung ATA 04
Operation in Cold Weather Conditions and Low Altitude
bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Fristen:
Manufacturer(s): Rolls-Royce Turbomeca Ltd
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. Applicability: RTM322-01/9 turboshaft engines, all serial numbers, except those
incorporating the modification C3003 standard HP2 turbine blades.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA AD 2008-0025R1 vom 06.07.2009 These engines are known to be installed in, but not limited to, NH Industries
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen NH90 (military) helicopters.
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 Reason: During NH90 flight development testing an RTM322 engine suffered a
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
second stage high pressure (HP2) turbine blade rupture. Investigation by
Rechtsbehelfsbelehrung: Rolls-Royce Turbomeca (RRTM) concluded that the cause was a high cycle
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder fatigue (HCF) blade vibration phenomenon that can occur when the engine
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. is operated in low ambient temperatures at low pressure altitude.
LTAs werden auch im Internet unter http://www.lba.de publiziert An increase in gas pressure at these conditions can be sufficient to initiate
***
cracks in the HP2 turbine blade if the gas generator is operated at a speed
that causes vibration of the blade at its natural frequency. Loss of a HP2
turbine blade may lead to an in-flight shutdown (IFSD). As both engines on
the NH90 are exposed to similar conditions, there is the possibility of a
common-mode event and dual-IFSD. As a consequence of this event the
current RTM322–01/9 fleet is subject to a flight envelope restriction that
limits engine operation at low ambient temperatures and low pressure
altitudes. Recently, there have been additional occurrences of HP2 turbine
blade cracking or rupture in other RTM322 variants. RRTM has therefore re-
assessed the risk associated with this event and has developed a further
flight envelope restriction on the RTM322-01/9 engine.
EASA Form 110 Page 1/2
(LTA-Nr.: D-2008-084 vom 03.03.2008) Aktenzeichen: (10)T23-502.1/D-2008-084R1 Seite 1 von 1
EASA AD No.: 2008-0025R1
For the reasons stated above, this Airworthiness Directive (AD) requires the Lufttüchtigkeitsanweisung
implementation of a flight envelope restriction on RTM322-01/9 engines.
This revised AD has been issued to introduce Modification C3003 as an optional
LTA-Nr.: D-2008-132R1
terminating action to the AD. ersetzt: D-2008-132
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 14.08.2009
Effective Date: 26 February 2008
Muster: Rolls-Royce AD der ausländischen Behörde:
RB211 EASA AD 2008-0045-CN (Cancellation Notice) vom 09.07.2009
Required Action(s) Required as indicated unless accomplished previously:
and Compliance Geräte-Nr.: Technische Mitteilungen des Herstellers:
Before next flight after the effective date of this AD, implement the revised 6315, CAAUK TCDS 1044 -keine-
Time(s):
flight envelope restriction:
Engine operation is no longer permitted within Zone A defined in figure 1 of Betroffenes Luftfahrtgerät:
RRTM Alert Service Bulletin SBP-M3-A-04-40-00-01A-A-A.
For engines that have previously been operated in Zone A, the information Rolls-Royce
defined within the Alert Service Bulletin must be provided to RRTM. RRTM RB211
will then assess whether operation can continue and advise what inspections
are required. Pending such assessment by RRTM and completion of the - Baureihen: RB211-535E4-37
required inspections, no further flight is permitted. RB211-535E4-B-37
RB211-535E4-C-37
A re-designed HP2 Turbine Blade is available as modification C3003 which
removes the risk of blade cracking due to operation at low temperature and - Werk-Nrn.: Alle Triebwerke der genannten Baureihen in denen folgende Niederdruckturbinen-
at low altitude. scheiben eingebaut sind:
Ref. Publications: Rolls-Royce Turbomeca Ltd Alert Service Bulletin SBP-M3-A-04-40-00-01A- LP Turbine Stage 1 Disc, P/N UL18946, mit der Seriennummer
A-A. EETM5398
The use of later approved revisions of this document is acceptable for
compliance with the requirements of this AD. LP Turbine Stage 1 Disc, P/N UL29028, mit den Seriennummern
EETM4365, EETM4845, EETM5620, EETM5639,
1. If requested and appropriately substantiated, EASA can accept EETM5762, EETM5755, SETM13799
Remarks :
Alternative Methods of Compliance for this AD.
LP Turbine Stage 2 Disc, P/N FW16687, mit der Seriennummer
2. The original AD was posted on 11 January 2008 as PAD 08-002 for SETM2336/A
consultation until 08 February 2008. No comments were received during
this period. LP Turbine Stage 2 Disc, P/N FW16688, mit der Seriennummer
3. Enquiries regarding this AD should be referred to the AD Focal Point - SEBH5124
Certification Directorate, EASA. E-mail: ADs@easa.europa.eu
LP Turbine Stage 2 Disc, P/N FW16689, mit den Seriennummern
4. For any question concerning the technical content of the requirements in SETM05358, SETM06287
this AD, please contact:
Rolls-Royce plc, PO Box 3, Filton, BS34 7QE, England; LP Turbine Stage 2 Disc, P/N UL29029, mit den Seriennummern
Telephone: +44 (0) 117 97 90700; Fax: +44 (0) 117 97 95498 SETM09300/A, SETM09260/A, SETM09697/A,
SETM13730, SETM14501
LP Turbine Stage 3 Disc, P/N UL29031, mit den Seriennummern
SETY01673, SETY01882, SETY02100, SETY02556
SETY02653, SETY02981, SETY03690, SETY03636
Betrifft:
Möglicher Triebwerksausfall im Fluge durch Bruch von Niederdruckturbinenscheiben infolge unentdeckter
Rißbildung.
Maßnahmen:
Aufgrund der ''Cancellation Notice'', die die europäische Luftfahrtagentur EASA mit der Airworthiness
Directive 2008-0045-CN am 09.07.2009 bekannt gegeben hat, wird die Lufttüchtigkeitsanweisung
D-2008-132 vom 19.03.2008 aufgehoben.
Fristen:
Die Lufttüchtigkeitsanweisung D-2008-132 vom 19.03.2008 wird mit sofortiger Wirkung aufgehoben.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA AD 2008-0045-CN (Cancellation Notice) vom 09.07.2009
EASA Form 110 Page 2/2
(LTA-Nr.: D-2008-132 vom 19.03.2008) Aktenzeichen: (10)T23-502.1/D-2008-132R1 Seite 1 von 2
EASA AD Cancellation Notice No.: 2008-0045-CN
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 AIRWORTHINESS DIRECTIVE
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es EASA
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen. CANCELLATION NOTICE
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder AD No.: 2008-0045-CN
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
LTAs werden auch im Internet unter http://www.lba.de publiziert
*** Date: 09 July 2009
Note: This Airworthiness Directive Cancellation Notice 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.
Type Approval Holder’s Name: Type/Model designation(s):
ROLLS-ROYCE PLC RB211-535E4 Series Engines
TCDS Number: United Kingdom TCDS No. 1044
Foreign AD: Not applicable
Supersedure: Cancels EASA AD 2008-0045 dated 13 March 2008.
Engine – Low Pressure (LP) Turbine Discs –
ATA 72
Identification / Inspection
Manufacturer(s): Rolls-Royce plc
Applicability: Models RB211-535E4-37, RB211-535E4-B-37 and RB211-535E4-C-37
engines, all serial numbers, if parts identified in Table 1 of EASA AD 2008-
0045 are installed.
These engines are known to be installed on, but not limited to, Boeing 757
series aircraft.
Reason: According to information provided by Rolls-Royce plc to EASA the
mandated actions required by EASA AD 2008-0045 have been carried out
on all affected LP Turbine Stage Discs.
For the reasons described above, AD 2008-0045 is cancelled.
Effective Date: 09 July 2009
Compliance Not applicable
Ref. Publications: Not applicable
Remarks: 1. Enquiries regarding this AD Cancellation Notice should be referred to
the AD Focal Point - Airworthiness Directives, Safety Management &
Research Section, Certification Directorate, EASA.
E-mail: ADs@easa.europa.eu
EASA Form 116 Page 1/2
(LTA-Nr.: D-2008-132 vom 19.03.2008) Aktenzeichen: (10)T23-502.1/D-2008-132R1 Seite 2 von 2
EASA AD Cancellation Notice No.: 2008-0045-CN
2. For any questions concerning the technical content of this AD Lufttüchtigkeitsanweisung
Cancellation Notice, please contact: LTA-Nr.: D-2008-400R1
Rolls-Royce plc., P.O. Box 31, Derby, DE24 8BJ, United Kingdom;
Telephone: +44 (0) 1332 242424, Fax: +44 (0) 1332 249936; ersetzt: D-2008-400
Luftfahrt-Bundesamt
Email: tech.help@rolls-royce.com or download the publication from Datum der Bekanntgabe: 10.08.2009
https://www.aeromanager.com/
Muster: Eurocopter AD der ausländischen Behörde:
SA 330 F EASA EAD 2009-0178-E vom 07.08.2009
Geräte-Nr.: Technische Mitteilungen des Herstellers:
3043, EASA.R.002 Eurocopter AS332 Alert Service Bulletin 25.02.08 Revision 1 vom
03.08.2009
Eurocopter SA330 Alert Service Bulletin 25.39 Revision 1 vom
03.08.2009
Betroffenes Luftfahrtgerät:
Eurocopter
SA 330 F
- Baureihen: AS 332 C, AS 332 C1, AS 332 L, AS 332 L1 und AS 332 L2
SA 330 F, SA 330 G und SA 330 J
- Werk-Nrn.: Nähere Angaben zu betroffenen Helikoptern können der genannten EASA Emergency
Airworthiness Directive entnommen werden.
Betrifft:
Equipment & Furnishings – Hydraulic Hoist Cable – Limitation / Modification
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
Airworthiness Directive und den genannten technischen Mitteilungen 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.
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.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA EAD 2009-0178-E vom 07.08.2009
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
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.
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 116 Page 2/2
(LTA-Nr.: D-2008-400 vom 22.12.2008) Aktenzeichen: (02)T23-502.1/D-2008-400R1 Seite 1 von 1
EASA AD No.: 2009-0178-E EASA AD No.: 2009-0178-E
implementation of a temporary limitation on hoist operation in case of cable
EASA EMERGENCY AIRWORTHINESS DIRECTIVE jamming and required installation of a lower hoist beam fitting protector to
prevent the hoist cable jamming against the base of the supporting strut.
AD No.: 2009-0178-E
Since AD 2008-0222-E was published, a detailed configuration review showed
that some civilian SA 330 helicopters may also be fitted with hoist beam P/N
330A87-2345 (dash numbers -00 to -06 inclusive). In addition, it has been
noticed that some helicopters (SA 330 or AS 332) may have their hoist control
Date: 07 August 2009
electrical harness routed in the same area of the supporting strut where the
Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance
hoist cable jammed during the first incident. Should this electrical harness be
with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States damaged due to hoist cable jamming, this other condition, if not corrected,
and of the European third countries that participate in the activities of EASA under Article 66 of could lead to untimely firing of the hoist pyrotechnic squib, thereby shearing the
that Regulation cable, possibly resulting in personal injuries and/or damage to the helicopter.
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 For the reasons described above, this new EASA AD retains for AS 332
an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency helicopters the requirements of AD 2008-0222-E, which is superseded, and
[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]. extends the applicability to include SA 330 helicopters. It also requires disabling
the hoist pyrotechnic shear function of some helicopters and the implementation
Type Approval Holder’s Name : Type/Model designation(s) : of an additional limitation, pending modification. This AD also allows, under
certain conditions, continued operation of the helicopter without modification.
EUROCOPTER AS 332 and SA 330 helicopters
Effective Date: 11 August 2009
TCDS Number : EASA.R.002
Required as indicated, unless accomplished previously:
Foreign AD : Not applicable
(1) For all helicopters as identified in the Applicability of this AD, pending
installation of a lower hoist beam fitting protector:
Supersedure : This AD supersedes EASA AD 2008-0222-E dated 19 December 2008.
(1.1) Before the next hoist operation after the effective date of this AD,
install a placard in full view of the hoist operator, stating the following:
Equipment & Furnishings – Hydraulic Hoist Cable – Limitation /
ATA 25 IN CASE OF CABLE JAM AGAINST STRUT
Modification
DO NOT ATTEMPT TO RAISE OR LOWER LOAD
Note: If the cable jams against the supporting strut following large oscillations,
Manufacturer(s): Eurocopter (formerly Eurocopter France, Aerospatiale, Sud Aviation) no attempt should be made to raise or lower the load, in order to minimize the
risk of damaging the cable and potentially severing it.
AS 332 C, AS 332 C1, AS 332 L, AS 332 L1 and AS 332 L2 helicopters, all
serial numbers, if equipped with a hoist beam Part Number (P/N) 330A87-2345 (1.2) In case cable jamming occurs, before the next hoist operation, check
(dash numbers -00 to -06 inclusive), in combination with a tray-mounted single the condition of the cable in accordance with the instructions of the
or double hoist, and which do not embody modification (MOD) 332A081113.00. applicable Component Maintenance Manual and, in case damage is
Required Action(s)
Applicability: found, take corrective actions accordingly.
SA 330 F, SA 330 G and SA 330 J helicopters, all serial numbers, if equipped and Compliance
with a hoist beam P/N 330A87-2345 (dash numbers -00 to -06 inclusive), in Time(s):
(1.3) For those helicopters with a hoist control electrical harness routed at
combination with a tray-mounted single hoist. the base of the hoist supporting strut, before the next hoist operation
after the effective date of this AD:
Note: The hoist beam P/N is engraved in the center of the strut assembly.
(1.3.1) Disable the hoist pyrotechnic shear function, in accordance
An incident has been reported of a hydraulic hoist cable jamming against the with the instructions of paragraph 2.B.3 of Eurocopter AS332
base of the supporting strut of a dual hoist tray installation. The jamming Alert Service Bulletin 25.02.08 Revision 1 or Eurocopter
occurred during a rescue at sea, while the load was lifted and subject to large SA330 ASB 25.39 Revision 1 (the applicable ASB); and
oscillations. The load was transferred to the backup electrical hoist and safely
brought onboard. However, when jamming against the hoist supporting strut, (1.3.2) Insert a copy of the Appendix 1 of the applicable ASB into the
the hydraulic hoist cable damaged the back-up electrical hoist power supply applicable Rotorcraft Flight Manual (RFM); and
Reason: harness which is routed through that area, resulting in a short circuit that fused
and ruptured the hydraulic hoist cable. (1.3.3) Install 2 placards, in full view of the flight crew and the hoist
operator respectively, stating the following:
This condition, if not corrected, could lead to further incidents of hoist cable
jamming and consequent cable failure, possibly resulting in personal injuries x on the instrument panel,
and/or damage to the helicopter.
HOIST PYROTECHNIC SHEAR FUNCTION DISABLED
EASA initially issued Emergency AD 2008-0222-E, which required the
EASA Form 111 Page 1/4 EASA Form 111 Page 2/4
EASA AD No.: 2009-0178-E EASA AD No.: 2009-0178-E
x near the hoist operator station, (4) For helicopters operated in accordance with paragraph (1.3) of this
AD:
HOIST PYROTECHNIC SHEAR FUNCTION DISABLED
IN CASE OF NECESSITY, CUT THE HOIST CABLE After modification of a helicopter in accordance with paragraph (2.1.1),
WITH THE SHEARS LOCATED IN THE CABIN (2.2.1) or (3.1), as applicable, before the next hoist operation, remove the
RFM changes (paragraph 1.3.2 of this AD) and the placards (paragraph
(2) For AS 332 helicopters: (1.3.3) of this AD) and re-establish the hoist pyrotechnic shear function of
that helicopter in accordance with the instructions of paragraph 2.B.2.e of
(2.1) On AS 332 helicopters equipped with a tray-mounted double hoist with the applicable ASB.
the back-up electrical hoist power supply harness routed at the base
of the hoist supporting strut, before next flight, accomplish either Eurocopter AS332 ASB 25.02.08 Revision 1 dated 03 August 2009.
(2.1.1) or (2.1.2) below:
Eurocopter SA330 ASB 25.39 Revision 1 dated 03 August 2009.
Ref. Publications:
(2.1.1) Install a protection of the base of the hoist strut assembly in
accordance with the instructions of paragraph 2.B.2 of the The use of later approved revisions of these documents is acceptable for
applicable ASB (MOD 332A081113.00). compliance with the requirements of this AD.
(2.1.2) Install placards in full view of the flight crew and the hoist 1. If requested and appropriately substantiated, EASA can approve Alternative
operator, stating the following: Methods of Compliance for this AD.
IN-FLIGHT OPERATION OF THE HOIST IS PROHIBTED 2. The safety assessment has requested not to implement the full consultation
process and an immediate publication and notification.
After modification of a helicopter in accordance with
paragraph (2.1.1.), remove the placards, including the one 3. Enquiries regarding this AD should be referred to the Airworthiness
required by paragraph (1.1) of this AD. Remarks : Directives, Safety Management & Research Section, Certification
Directorate, EASA. E-mail: ADs@easa.europa.eu.
(2.2) On all other AS 332 helicopters, except if equipped with a RH side
sliding door P/N 332A22-1165-01, not later than 31 December 2009, 4. For any question concerning the technical content of the requirements in
accomplish either (2.2.1) or (2.2.2) below: this AD, please contact:
EUROCOPTER (STDI) – Aéroport de Marseille Provence 13725 Marignane
(2.2.1) Install a protection of the base of the hoist strut assembly in Cedex, France; telephone +33 (4) 12 85 97 97; facsimile +33 (4) 85 99 66;
accordance with approved instructions. Modification of a E-mail: Directive.technical-support@eurocopter.com
helicopter in accordance with paragraph 2.B.2 of the
applicable ASB (MOD 332A081113.00) is an acceptable
method of compliance with this requirement.
(2.2.2) Install placards in full view of the flight crew and the hoist
operator, stating the following:
IN-FLIGHT OPERATION OF THE HOIST IS PROHIBTED
After modification of a helicopter in accordance with
paragraph (2.2.1.), remove the placards, including the one
required by paragraph (1.1) of this AD.
(3) For SA 330 helicopters: Not later than 31 December 2009, accomplish
either (3.1) or (3.2) below:
(3.1) Install a protection of the base of the hoist strut assembly in
accordance with approved instructions.
(3.2) Install placards in full view of the flight crew and the hoist operator,
stating the following:
IN-FLIGHT OPERATION OF THE HOIST IS PROHIBTED
After modification of a helicopter in accordance with paragraph (3.1),
remove the placards, including the one required by paragraph (1.1) of
this AD.
EASA Form 111 Page 3/4 EASA Form 111 Page 4/4
EASA AD No.: 2009-0072R1
Lufttüchtigkeitsanweisung EASA AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2009-078R1
AD No.: 2009-0072R1
ersetzt: D-2009-078
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 07.08.2009
Muster: PZL AD der ausländischen Behörde:
PZL-104 ''Wilga 35'' EASA AD 2009-0072R1 vom 25.06.2009 Date: 25 June 2009
PZL-104 ''Wilga 80''
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
Geräte-Nr.: Technische Mitteilungen des Herstellers: of the European third countries that participate in the activities of EASA under Article 66 of
745, EASA.A.061 1. EADS PZL Mandatory Bulletin Nr. 1109185 vom 18.03.2009 that Regulation.
2. EADS PZL Mandatory Bulletin Nr. 10409036 vom 18.03.2009 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
3. AMM "Maintenance Instructions and Scheduled Inspections" continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate
von 1981 für PZL-104 Wilga 35 von Seriennr. 48031 bis 74217. 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 of Registry
4. AMM "Maintenance Instructions and Scheduled Inspections" [EC 216/2008, Article 14(4) exemption].
Issue B von 1975 für PZL-104 Wilga 35 von Seriennr. 85218 und
folgende. Type Approval Holder’s Name : Type/Model designation(s) :
5. AMM "Maintenance Instructions and Scheduled Inspections"
Issue C von 1982 für PZL-104 Wilga 35A von Seriennr. 16820629 EADS PZL 'Warszawa-Okcie' S.A. PZL-104 Wilga 35 series and Wilga 80
und folgende. aeroplanes
6. AMM "Maintenance Instructions and Scheduled Inspections"
von 1980 für EADS PZL-104 Wilga 80.
TCDS Number : EASA A.061
Betroffenes Luftfahrtgerät:
Foreign AD : Not applicable
PZL
PZL-104 ''Wilga 35'', PZL-104 ''Wilga 80''
Revision : This directive revises AD 2009-0072 dated 31 March 2009
- Baureihen: PZL-104 Wilga 35, 35A und 80
- Werk-Nrn.: Alle
Fuselage - Maintenance Programme and Fuselage Front Posts -
ATA 53
Inspection / Repair
Betrifft:
Fuselage - Maintenance Programme and Fuselage Front Posts - Inspection / Repair
Maßnahmen: Manufacturer(s): EADS PZL “Warszawa-Okcie” S.A.
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
Airworthiness Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen. Applicability: Model PZL-104 Wilga 35, 35A and 80 aeroplanes, all serial numbers.
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente Reason: An inspection of a PZL-104 aeroplane that had a relatively long operational
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits- background revealed a severe corrosion of the steel front fuselage structural
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt. elements.
It is likely that such corrosion can also be present on other aeroplanes of similar
Fristen: design and operational history.
Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen.
If left uncorrected, this condition could lead to loss of strength of the structural
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
front posts elements and consequent reduction of the structural strength of the
EASA Airworthiness Directive. aeroplane.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der For the reason stated above, this Airworthiness Directive (AD) mandates
EASA AD 2009-0072R1 vom 25.06.2009 inspecting the fuselage front posts, repairing any corrosion found and replacing
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen pads made of foam rubber by pads made of Neoprene to prevent water
nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der ingression.
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. This revision 1 extends the compliance time from 2 to 6 months to ensure
availability of replacement parts and clarifies the criteria for corrosion damage
Rechtsbehelfsbelehrung: related to the paragraph (1.2) of this AD.
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.
Effective Date: 14 April 2009
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
EASA Form 110 Page 1/2
(LTA-Nr.: D-2009-078 vom 01.04.2009) Aktenzeichen: (01)T23-502.1/D-2009-078R1 Seite 1 von 1
EASA AD No.: 2009-0072R1
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) For aeroplanes which have accumulated 12 years or more from the last
Lufttüchtigkeitsanweisung
Time(s): overhaul at the effective date of this AD: LTA-Nr.: D-2009-079R1
(1.1) Within six months after the effective date of this AD, inspect for signs of ersetzt: D-2009-079
corrosion the fuselage front posts as instructed in paragraph 6.A. of Luftfahrt-Bundesamt
EADS PZL “Warszawa-Okcie” S. A. Mandatory Bulletin (MB)
Datum der Bekanntgabe: 07.08.2009
No.1109185 initial issue for PZL-104 Wilga 35 and 35A aeroplanes Muster: Eurocopter AD der ausländischen Behörde:
and No.10409036 initial issue for PZL-104 Wilga 80 aeroplanes. EC 155 EASA AD 2009-0078R1 vom 30.06.2009
(1.2) if serious corrosion/corrosion damage is found during the inspection Geräte-Nr.: Technische Mitteilungen des Herstellers:
required in paragraph (1.1) of this AD, before further flight, repair or 3052, DGAC TCDS 159 1. EUROCOPTER EC155 Alert Service Bulletin Nr. 04A009 vom
replace any parts in accordance with an approved repair solution or 30.03.2009
airworthy part respectively.
2. EUROCOPTER EC155 Alert Service Bulletin Nr. 04A009
Note: For the purpose of this AD, serious corrosion/corrosion damage is a Revision 1 vom 24.06.2009
corrosion finding that meets the criteria as defined in paragraph 6.A.c of the 3. EUROCOPTER EC155 Service Bulletin Nr. 25-095 vom
Service Bulletins given in reference. 25.06.2009
(1.3) Within six months after the effective date of this AD, replace the
padding of the rear glass as instructed in paragraph 6.C. of EADS PZL Betroffenes Luftfahrtgerät:
MB No.1109185 initial issue for PZL-104 Wilga 35 and 35A
aeroplanes and MB No. 10409036 initial issue for PZL-104 Wilga 80 Eurocopter
aeroplanes. EC 155
(2) For all aeroplanes:
- Baureihen: EC 155 B und B1
Within six months after the effective date of this AD, amend the approved
operator’s aeroplane maintenance programme to incorporate the applicable - Werk-Nrn.: Alle Helikopter dieser Baureihen bis Werknummer (S/N) 6892 ausgerüstet mit
tasks as described in the relevant PZL-104 Wilga 35 or PZL-104 Wilga 80
''VIP 4-Seat Bench'' mit den Hersteller-Teilenummern (P/N's) 365V85-0045-01 oder
Maintenance Manuals titled ‘Maintenance Instructions and Scheduled
365V85-0046-01.
Inspections’ given in reference.
Ref. Publications: EADS PZL “Warszawa-Okcie” S. A. Mandatory Bulletin No.1109185 Hinweis:
initial issue dated 18 March 2009, Helikopter mit der Hersteller-Modifikation 365V080079.01 und/oder 365V080079.02 sind
von dieser LTA nicht betroffen.
EADS PZL “Warszawa-Okcie” S. A. Mandatory Bulletin No.10409036
initial issue dated 18 March 2009;
Betrifft:
The use of later approved revisions of these documents is acceptable for Equipment / Furnishings – VIP 4-seat Benches – Limitation
compliance with the requirements of this AD.
Aeroplane Maintenance Manual (AMM) ‘Maintenance Instructions and Maßnahmen:
Scheduled Inspections’ issue dated 1981 for PZL-104 Wilga 35 from serial Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
number (s/n) 48031 to 74217, issue B dated 1975 for PZL-104 Wilga 35 from s/n Airworthiness Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen.
85218 onwards, and issue C dated 1982 for PZL-104 Wilga 35A from s/n Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
16820629 onwards. vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
AMM ‘Maintenance Instructions and Scheduled Inspections’ dated 1980 for anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
EADS PZL-104 Wilga 80.
Fristen:
Remarks : 1. If requested and appropriately substantiated, EASA can approve Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen.
Alternative Methods of Compliance for this AD. Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
2. The required actions and the risk allowance have granted the issuance EASA Airworthiness Directive.
of a Final AD with Request for Comments, postponing the public
consultation process after publication. Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA AD 2009-0078R1 vom 30.06.2009
3. Enquiries regarding this AD should be referred to the Airworthiness Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
Directives, Safety Management & Research Section, Certification nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der
Directorate, EASA. E-mail ADs@easa.europa.eu 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.
4. For any questions concerning the technical content of the requirements
in this AD, please contact: Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
EADS PZL “Warszawa-Okcie” S.A. zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
Aleja Krakowska 110/114 - 00-971 Warszawa - Poland
LTAs werden auch im Internet unter http://www.lba.de publiziert
Phone: +48 22 577 22 11 Fax: +48 22 577 22 03 ***
E-mail: eadspzl@pzl.eads.net
EASA Form 110 Page 2/2
(LTA-Nr.: D-2009-079 vom 02.04.2009) Aktenzeichen: (02)T23-502.1/D-2009-079R1 Seite 1 von 1
EASA AD No.: 2009-0078R1 EASA AD No.: 2009-0078R1
EASA AIRWORTHINESS DIRECTIVE Required as indicated, unless accomplished previously:
(1) Before next flight after the effective date of this AD, amend the RFM of the
AD No.: 2009-0078R1 affected helicopters as follows:
The VIP 4-seat bench must be limited to 3 PAX.
Date: 30 June 2009 Inserting a copy of this AD into the RFM is an acceptable method to
comply with this requirement.
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 of the
European third countries that participate in the activities of EASA under Article 66 of that
(2) At the latest at the next flight-related check [which is defined as every 15
Regulation Required Action(s) flight hours or 7 days, whichever occurs first] after the effective date of this
and Compliance AD, convert the VIP 4-seat bench into a 3-seat bench in accordance with
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 Time(s): the instructions of paragraph 2.B.2 of Eurocopter EC 155 Alert Service
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 Bulletin (ASB) No 04A009.
[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].
Optional Terminating Action:
Type Approval Holder’s Name : Type/Model designation(s) :
(3) After modification of a helicopter by installing kit 365V080079.01 (rear
EUROCOPTER EC 155 helicopters bench) and/or kit 365V080079.02 (front bench), as applicable to interior
configuration, in accordance with the instructions of Eurocopter EC 155
Service Bulletin (SB) 25-095, the RFM limitation imposed by paragraph (1)
TCDS Number : DGAC France No 159
of this AD is no longer required for that helicopter and the VIP 4-seat bench
conversion into a 3-seat bench as required by paragraph (2) of this AD can
Foreign AD : Not applicable be reversed.
Revision : This AD revises and replaces EASA Emergency AD 2009-0078-E dated Eurocopter EC 155 ASB No. 04A009 original issue dated 30 March 2009 or
01 April 2009. Revision 1 dated 24 June 2009
Ref. Publications: Eurocopter EC 155 SB No. 25-095 dated 25 June 2009.
ATA 25 Equipment / Furnishings – VIP 4-seat Benches – Limitation The use of later approved revisions of these documents is acceptable for
compliance with the requirements of this AD.
Manufacturer(s): Eurocopter 1. If requested and appropriately substantiated, EASA can approve Alternative
Methods of Compliance for this AD.
EC 155 B and B1 helicopters, all serial numbers up to 6892 inclusive, if fitted
2. The original issue of this AD was published as an Emergency AD. The
Applicability: with a VIP 4-seat bench Part Number (P/N) 365V85-0045-01 or P/N 365V85-
safety assessment has requested not to implement the full consultation
0046-01.
process and an immediate publication and notification.
It has been noted by Eurocopter during new customization work consisting in 3. Enquiries regarding this AD should be referred to the Airworthiness
installing a VIP bench seat that the load strength of the fixed parts of the Remarks :
Directives, Safety Management & Research Section, Certification
installation did not meet the certification specifications. Directorate, EASA. E-mail: ADs@easa.europa.eu.
This condition, if not corrected, would lead, in case of an emergency landing, to 4. For any question concerning the technical content of the requirements in
overloading of the seat structure at the attachment point. Structural overload this AD, please contact: EUROCOPTER (STDI) – Aéroport de Marseille
could cause the seat bench insert to be torn from the floor fitting rails, detaching Provence 13725 Marignane Cedex, France
the seat bench from the floor, potentially resulting in injury to the seat telephone +33 (4) 12 85 97 97, facsimile +33 (4) 42 85 99 66
occupants. E-mail: Directive.technical-support@eurocopter.com
Reason:
For the reason described above, this AD requires the implementation of a
limitation by reducing the use of the affected seat bench to three passengers,
ensuring that structural strength is within required margins.
This AD has been revised to confirm that incorporation of modification kit
365V080079.01 (rear bench) and/or kit 365V080079.02 (front bench), as
applicable to interior configuration, constitutes terminating action for the
Rotorcraft Flight Manual (RFM) limitation imposed by this AD.
Effective Date: 03 April 2009
EASA Form 110 Page 1/2 EASA Form 110 Page 2/2
