Nachrichten für Luftfahrer 2004 Teil II (weicht ggf. von Druckversion ab)
AIRWORTHINESS
United Kingdom
Civil Aviation Authority DIRECTIVE
AD No: G-2004-0010
Issue Date: 8 April 2004
This AD is issued by the UK CAA acting for and on behalf of the European Aviation Safety Agency as the Primary Aviation Authority (ICAO
Annex 8 Authority of State of Design) for the affected product(s).
Approved by the European Aviation Safety Agency under approval number 2004-3674 on 7 April 2004.
In accordance with Article 9(7)(b) of the Air Navigation Order 2000 as amended the following action required by this Airworthiness Directive
(AD) is mandatory for applicable aircraft registered in the United Kingdom.
No person may operate an aircraft to which an AD applies except in accordance with the requirements of that AD unless otherwise agreed
with the Authority of the State of Registry.
Type Approval Holders Name: Type/Model Designation(s):
ROLLS-ROYCE PLC RB211 TRENT 768-60, 772-60, 772B-60
Type Certificate Data Sheet No: 1050
Superseded AD: G-2003-0014
ATA 72 – ENGINE – HP COMPRESSOR – TEST/MODIFICATION
Manufacturer(s): Rolls-Royce plc
Applicability: Models RB211 Trent 768-60, 772-60 and 772B-60 engines installed on Airbus A330 aeroplanes.
Reason: There have been a number of low power surges in service on Trent 700 engines. These surges
occurred with the aeroplane on the ground as take-off power was being set or during taxi. The cause of the
surges has been identified as excessive wear on the HPC casing front location feature. This causes increased
HPC tip clearances resulting in loss of surge margin. Engines affected by this problem are also at risk of failure
to respond due to surge on acceleration during descent, prior to flap selection.
Routine ground testing for adequate surge margin will assure safe in-flight operation and embodiment of the
redesigned HPC casing front location feature will remove the problem.
This AD supersedes AD G-2003-0014 by introducing the accomplishment of the engine control software to
automatically maximise HPC surge margin in descent as an Interim Action with an associated compliance date.
The requirements of this AD are otherwise unchanged from those of AD G-2003-0014.
Effective Date: 4 December 2003 (the effective date of AD G-2003-0014).
Compliance/Action:
1) In-Service Test
Carry out a surge test in accordance with Rolls-Royce Alert Service Bulletin RB211-71-AD509 revision 3 or later
CAA approved revision, Section 3 Accomplishment Instructions before the engine exceeds 2000 cycles since
new or 1000 cycles since HP Compressor overhaul, and subsequently at intervals of not more than;
(a) 130 cycles
or
(b) 160 cycles if Rolls-Royce Alert Service Bulletin RB211-73-AE224 original issue or later CAA approved
revision, or later standard of engine control software is embodied.
Note: For the purposes of this Airworthiness Directive, testing carried out in accordance with superseded AD 005-
09-2001 or AD G-2003-0014 (Rolls-Royce Alert Service Bulletin RB211-71-AD509 revision 3, revision 2, revision
1 or original issue) is deemed to be valid.
continued on next page
G-2004-0010 page 2 of 2 2) Interim Action Fit an EEC incorporating a revised standard of engine control software as specified in Rolls-Royce Alert Service Bulletin RB211-73-AE224 original issue or later CAA approved revision, or later standard of engine control software, before 1 July 2005. 3) Terminating Action Fit redesigned HP compressor stage 1 casing and intermediate case outer location ring in accordance with Rolls- Royce Service Bulletin RB211-72-D574 original issue or later CAA approved revision, Section 3 Accomplishment Instructions within 4500 cycles of the Effective Date of this Airworthiness Directive or before 30 June 2012 whichever is the sooner. Incorporation of this modification removes the requirement to carry out 1) In-Service Test and 2) Interim Action and therefore constitutes the terminating action for this Airworthiness Directive. Reference Publications: Rolls-Royce Alert Service Bulletin RB211-71-AD509 revision 3 or later approved issue, Rolls-Royce Alert Service Bulletin RB211-73-AE224 original issue or later CAA approved revision, Rolls- Royce Service Bulletin RB211-72-D574 original issue or later CAA approved revision may be obtained from Publication Services, Rolls-Royce plc, PO Box 31, Derby, DE24 8BJ, United Kingdom. Phone: +44 (0) 1332 242424 Fax: +44 (0) 1332 249936. Remarks: Enquiries regarding this AD may be directed to Civil Aviation Authority, Safety Regulation Group, Propulsion Department, Aviation House, Gatwick Airport South, West Sussex, RH6 0YR, United Kingdom. Phone: +44 (0) 1293 573199 Fax: +44 (0) 1293 573979 E-mail: tony.boud@srg.caa.co.uk.
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2003-414R1
ersetzt: D-2003-414
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 10.06.2004
Muster: Rolls-Royce AD der ausländischen Behörde:
RB211 Trent 800 CAA AD G-2004-0008 vom 29.04.2004
Geräte-Nr.: Technische Mitteilungen des Herstellers:
6334 Rolls-Royce Alert Service Bulletin RB211-72-AD344 Revision 7
Rolls-Royce Alert Service Bulletin RB211-72-AD347 Revision 6
Rolls-Royce Service Bulletin RB211-72-D672
Betroffenes Luftfahrtgerät:
Rolls-Royce
RB211 Trent 800
- Baureihen: RB211 TRENT 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, 895-17
- Werk-Nrn.: Gemäß den Angaben der AD der ausländischen Behörde.
Betrifft:
ATA 72 – ENGINE - FAN BLADE - LUBRICATION / MODIFICATION
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten AD der
ausländischen Behörde und der oben genannten Technischen Mitteilung des Herstellers zu entnehmen.
Fristen:
Alle anzuwendenden Fristen sind der o.g. AD der ausländischen Behörde zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der o. g. AD der
ausländischen Behörde.
Hinweis:
Seit dem 28.09.2003 ist die Verordnung (EG) Nr. 1702/2003 der Europäischen Union in Kraft.
Demnach sind gemäß Artikel 2 dieser Verordnung Lufttüchtigkeitsanweisungen des Entwicklungsstaates
für ausländische Lfz-Muster unmittelbar gültig. Solange die Europäische Agentur für Flugsicherheit (EASA)
noch kein eigenes Veröffentlichungsverfahren für Luttüchtigkeitsanweisungen bekanntgegeben hat,
werden solche ausländischen Lufttüchtigkeitsanweisungen ohne inhaltliche Änderungen per "Deckblatt-
LTA" durch das Luftfahrt-Bundesamt angeordnet.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
CAA AD G-2004-0008 vom 29.04.2004
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
***
(LTA-Nr.: D-2003-414 vom 25.12.2003) Aktenzeichen: (10)M121-502.1/D-2003-414R1 Seite 1 von 1
AIRWORTHINESS
United Kingdom
Civil Aviation Authority DIRECTIVE
AD No: G-2004-0008
Issue Date: 29 April 2004
This AD is issued by the UK CAA acting for and behalf of the European Aviation Safety Agency as the Primary Aviation Authority (ICAO Annex
8 Authority of State of Design) for the affected product(s).
Approved by the European Aviation Safety Agency under Approval Number 2004-2827 on 23 March 2004.
In accordance with Article 9(7)(b) of the Air Navigation Order 2000 as amended the following action required by this Airworthiness Directive
(AD) is mandatory for applicable aircraft registered in the United Kingdom.
No person may operate an aircraft to which an AD applies except in accordance with the requirements of that AD unless otherwise agreed
with the Authority of the State of Registry.
Type Approval Holders Name: Type/Model Designation(s):
ROLLS-ROYCE PLC RB211 TRENT 875-17, 877-17, 884-17,
884B-17, 892-17, 892B-17, 895-17
Type Certificate Data Sheet No: 1051
Superseded ADs: 001-02-2001 and G-2003-0015
ATA 72 – ENGINE – FAN BLADE – INSPECTION/LUBRICATION/MODIFICATION
Manufacturer(s): Rolls-Royce plc
Applicability: Models RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, 895-17 engines, fitted
with fan blades to Rolls-Royce Service Bulletin RB211-72-C629 (part numbers; FK30842, FK 30840, FK30838),
RB211-72-C905 (part numbers; FW12960, FW13175, FW12961, FW12962), RB211-72-D390 (part number;
FW18548), OR RB211-72-E044 (part number; FW23552) standards installed on Boeing 777 aeroplanes
certificated in any category.
Reason: There has been one incident of fan blade failure and several instances of fan blade roots found cracked
on Trent 800 engines in service. The cracking has been shown to be the result of significant operating stress
levels and a breakdown of lubrication between the fan blade root and the fan disc slot. Cracking can be avoided
by maintaining lubrication of the fan blade roots. A risk analysis has concluded that mandatory action instructing
fan blade root lubrication is necessary to avoid an unacceptable risk of a multiple fan blade failure, which would
be a potentially hazardous event.
Airworthiness Directive (AD) G-2003-0015 introduced reduced intervals between re-lubrications (iaw Rolls-Royce
Service Bulletin RB211-72-AD347) for SB72-C905, SB72-D390 and SB72-E044 standard fan blades. This
change was prompted by observations of poor blade root condition on service run engines, which showed that
the rate of deterioration of lubrication was higher than previously believed. A Terminating Action for SB72-C629
and SB72-C905 standard of fan blades was also introduced.
This AD (G-2004-0008) supersedes AD’s G-2003-0015 and 001-02-2001, and has been issued for the following
reasons:
a) To introduce re-lubrication of fan blade roots to Rolls-Royce Service Bulletin RB211-72-C905, 72-D390
and 72–E044 standards, which have never been removed since delivery of the new engine, to have a
1200 cycle threshold as stated in Rolls-Royce Service Bulletin RB211-72-AD347 R6.
b) To introduce the amended Mandatory repeat inspection requirements of Rolls-Royce Service Bulletin
RB211-72-AD344 R7, applicable to Rolls-Royce Service Bulletin RB211-72-C629 and –C905 standard
fan blades, thereby superseding the requirements of AD 001-02-2001.
continued on next page
G-2004-0008 page 2 of 4
Effective Date: 12 May 2004
Compliance/Action:
1) Inspection of Fan Blade Root (in accordance with R-R Alert Service Bulletin RB211-72-AD344 R7)
Fan blades to Rolls-Royce Service Bulletin RB211-72-C629 or RB211-72-C905 standards;
Inspect according to aeroplane type and engine rating combinations, on or before the threshold lives and
subsequent repeat intervals not exceeding the intervals specified in Tables 1,2,3 and 4 below. Note that fan
blades to Rolls-Royce Service Bulletin RB211-72-D390 (full form root profile) and RB211-72-D672 (laser
shock peen) are not subject to this inspection. Fan blades are to be inspected in accordance with Rolls-
Royce Alert Service Bulletin RB211-AD344 Revision 7, Section 3 Accomplishment Instructions.
TABLE 1 BLADES NOT FEATURING SB72-C905
B777 GROSS WEIGHT ENGINE INSPECTION
AEROPLANE (1000 lbs) RATING THRESHOLD REPEAT
CATEGORY (CYCLES) (CYCLES)
(1A) 660 892, 884B
-300 632,5 600 80
(1B) 656 895
-200ER
(2) 648 1200 100
-200ER 892,892B
632,5
(3A) 580 892, 884B 2000 600
-300
(3B) 555 884 2000 600
-200ER
(3C) 545 877 2000 600
-200 535 875
TABLE 2 BLADES NOT FEATURING SB72-C905 BUT RELUBRICATED AT 600 CYCLES FREQUENCY OR LESS
B777 GROSS WEIGHT ENGINE INSPECTION
AEROPLANE (1000 lbs) RATING THRESHOLD REPEAT
CATEGORY (CYCLES) (CYCLES)
(1A) 660 892, 884B
-300 632,5 600 80
(1B) 656 895
-200ER
(2) 648 892,892B 1200 100
-200ER
632,5
(3A) 580 892, 884B 2400 600
-300
(3B) 555 884 2400 600
-200ER
(3C) 545 877 2400 600
-200 535 875
continued on next page
G-2004-0008 page 3 of 4
TABLE 3 BLADES WHICH (a) INCLUDED SB72-C905 FROM NEW OR (b) WERE REWORKED TO SB72-
C905 AT LESS THAN 600 CYCLES SINCE NEW OR PREVIOUS REWORK TO SB72-C629 OR (c)
REWORKED TO SB72-C905 WITH VERIFIABLE RE-LUBRICATION AT INTERVALS NOT EXCEEDING 600
CYCLES
B777 AEROPLANE GROSS WEIGHT ENGINE INSPECTION
CATEGORY (1000 lbs) RATING THRESHOLD REPEAT
(CYCLES) (CYCLES)
(1A) 660 892, 884B
-300 632,5 600 100
(1B) 656 895
-200ER
(2) 648 892,892B 1200 125
-200ER
632,5
(3A) 580 892, 884B 2400 600**
-300
(3B) 555 884 2400 600**
-200ER
(3C) 545 877 2400 600**
-200
535 875
TABLE 4 BLADES REWORKED TO SB72-C905 AT GREATER THAN 600 CYCLES SINCE NEW OR PREVIOUS RE-
WORK TO SB72-C629
B777 AEROPLANE GROSS WEIGHT ENGINE INSPECTION
CATEGORY (1000 lbs) RATING THRESHOLD REPEAT
(CYCLES) (CYCLES)
(1A) 660 892, 884B
-300 632,5 600 100
(1B) 656 895
-200ER
(2) 648 892,892B 1200 125
-200ER
632,5
(3A) 580 892, 884B 2000 600
-300
(3B) 555 884 2000 600
-200ER
(3C) 545 877 2000 600
-200
535 875
2) Re-lubricate fan blade root (in accordance with R-R Alert Service Bulletin RB211-72-AD347 R6)
a) Fan blades to Rolls-Royce Service Bulletin RB211-72-C629, -C905, -D390, and -E044 standards;
Re-lubricate fan blade roots in accordance with Rolls-Royce Alert Service Bulletin RB211-72-AD347
Revision 6, Section 3 Accomplishment Instructions prior to achieving 600 cycles in service since new or last
re-lubrication. Subsequently, re-lubricate at repeat intervals not exceeding 600 cycles in service.
b) Fan blades to Rolls-Royce Service Bulletin RB211-72-C905, -D390, and -E044 standards which have never
been removed from the engine since delivery of the new engine;
Re-lubricate fan blade roots in accordance with Rolls-Royce Alert Service Bulletin RB211-72-AD347 revision
6, section 3 Accomplishment Instructions on first removal or prior to achieving 1200 cycles in service since
new. Subsequently, re-lubricate at repeat intervals not exceeding 600 cycles in service.
c) Fan blades to Rolls-Royce Service Bulletin RB211-72-C905, -D390, and -E044 standards with lives in
excess of 400 cycles since new (that are not covered by paragraph b), above) or since last re-lubrication at
the Effective Date of this AD, a one-off increased interval is permitted as follows;
Re-lubricate fan blade roots in accordance with Rolls-Royce Alert Service Bulletin RB211-72-AD347
Revision 6, section 3 Accomplishment Instructions prior to achieving a further 200 cycles in service, but not
to exceed 1200 cycles since new or since last re-lubrication. Subsequently, re-lubricate at repeat intervals
not exceeding 600 cycles in service.
continued on next page
G-2004-0008 page 4 of 4
3) Terminating Action (in accordance with Rolls-Royce Service Bulletin RB211-72-D672)
Fan blades to Rolls-Royce Service Bulletin RB211-72-C629 and RB211-72-C905;
Apply laser shock peen, Metco 58 and dry film lubricant (DFL) in accordance with Rolls-Royce Service
Bulletin RB211-72-D672 Initial Issue, Section 3 Accomplishment Instructions at next shop visit where the fan
blade is refurbished or overhauled, or prior to 31 December 2009, whichever occurs first. Incorporation of
this modification removes the Mandatory requirements to carry out Part 1, root inspection, and Part 2, root
re-lubrication, (refer to Remarks Section for details) detailed in the Compliance/Action section of this
Airworthiness Directive, and therefore constitutes the terminating action for this AD.
Note: There is currently no terminating action for fan blades to Rolls-Royce Service Bulletins RB211-72-D390
and RB211-72-E044 standards.
Note: Previous compliance with the inspection and lubrication tasks of ADs G-2003-0015, 001-03-2001 and 001-
02-2001 are, for the purposes of this Airworthiness Directive, deemed to be equivalent inspection and
lubrication tasks.
Reference Publications: Rolls-Royce Alert Service Bulletins RB211-72-AD344 Revision 7 and RB211-72-
AD347 Revision 6, and Rolls-Royce Service Bulletin RB211-72-D672 initial issue, may be obtained from
Publication Services, Rolls-Royce plc. PO Box 31, Derby, DE24 8BJ, United Kingdom. Phone: +44 (0) 1332
242424 Fax: +44 (0) 01332 249936
Note: Later EASA approved Service Bulletin issues than the issues quoted within are also considered to be
acceptable to meet the requirements of this Airworthiness Directive.
Remarks: Note that while the Terminating Action terminates the requirements of this AD, the re-lubrication
remains a recommended action by the manufacturer for SB72-D672 standard fan blades.
The fan blade part numbers associated with the Service Bulletin standards addressed above are as follows;
SB 72-C629 (Fan blade SB 72-C905 (Fan blade SB 72-D390 (Full form SB 72-E044 (Fan blade root
cutback root profile) Metco58 anti-fret coating) root profile fan blades) revised shear key slot)
FK30838 FW12960 FW18548 FW23552
FK30840 FW12961
FK30842 FW12962
FW13175
Enquiries regarding this AD should be directed to Civil Aviation Authority, Safety Regulation Group, Propulsion
Department, Aviation House, Gatwick Airport South, West Sussex, RH6 0YR, United Kingdom. Phone: +44 (0)
1293 573199 Fax: +44 (0)1293 573979 E-mail: pete.woollacott@srg.caa.co.uk.
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2004-111R1
ersetzt: D-2004-111
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 10.06.2004
Muster: Eurocopter AD der ausländischen Behörde:
AS 355 DGAC AD F-2002-280-068R1 vom 17.03.2004
Geräte-Nr.: Technische Mitteilungen des Herstellers:
3056 Eurocopter AS 355 Alert Service Bulletin No. 34.00.09
Betroffenes Luftfahrtgerät:
Eurocopter
AS 355
- Baureihen: AS 355 E, F, F1, F2 und N
- Werk-Nrn.: alle, ausgestattet mit HSI KI 525 A
Betrifft:
Navigation (''navigation - horizontal situation indicator KI 525 A'')
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten AD der
ausländischen Behörde und der oben genannten Technischen Mitteilung des Herstellers zu entnehmen.
Fristen:
Alle anzuwendenden Fristen sind der o.g. AD der ausländischen Behörde zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der o. g. AD der
ausländischen Behörde.
Hinweis:
Seit dem 28.09.2003 ist die Verordnung (EG) Nr. 1702/2003 der Europäischen Union in Kraft.
Demnach sind gemäß Artikel 2 dieser Verordnung Lufttüchtigkeitsanweisungen des Entwicklungsstaates für
ausländische Lfz-Muster unmittelbar gültig. Solange die Europäische Agentur für Flugsicherheit (EASA) noch
kein eigenes Veröffentlichungsverfahren für Luttüchtigkeitsanweisungen bekanntgegeben hat, werden solche
ausländischen Lufttüchtigkeitsanweisungen ohne inhaltliche Änderungen per "Deckblatt-LTA" durch das
Luftfahrt-Bundesamt angeordnet.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
DGAC AD F-2002-280-068R1 vom 17.03.2004
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
***
(LTA-Nr.: D-2004-111 vom 18.03.2004) Aktenzeichen: (02)M123-502.1/D-2004-111R1 Seite 1 von 1
D-2004-111R1
AIRWORTHINESS DIRECTIVE Distribution: Issue date: Page :
A March 17, 2004 1/2
No F-2002-280-068 R1
Direction This Airworthiness Directive is published by the DGAC : Translation of « Consigne de Navigabilité » of same
générale number.
on behalf of EASA, the Primary Airworthiness Authority for the
de X affected product.
In case of difficulty, reference should be made to
l’aviation the French issue.
civile as the Registration Airworthiness Authority for the affected
France aircraft..
GSAC No person may operate an aircraft to which an Airworthiness Directive applies,
publication except in accordance with the requirements of that Airworthiness Directive,
unless otherwise agreed with the Authority of the State of Registry.
Corresponding foreign Airworthiness Directive(s): Airworthiness Directive(s) replaced:
Not applicable 2002-280-068 original issue
Person in charge of airworthiness: Type(s):
EUROCOPTER AS 355 helicopters
Type certificate(s) No. 168
TCDS No 168
ATA chapter: Subject:
34 Navigation - Horizontal situation indicator KI 525A
1. EFFECTIVITY:
AS 355 helicopter versions E, F, F1, F2 and N, equipped with HSI KI 525A.
2. REASONS:
This Airworthiness Directive (AD) is issued following the discovery of incorrect installation of HSI KI 525A,
part number 066-3046-07 (non-compliance with equipment manufacturer ALLIEDSIGNAL Service Bulletin
No. 341), which might result in navigation errors.
Revision 1 of this AD covers the conversion of EUROCOPTER AS 355 Alert Telex No. 34.00.09 into an
Alert Service Bulletin (ASB) with the same reference number, with no change to the technical content.
3. MANDATORY ACTIONS AND COMPLIANCE TIMES:
The following measures were rendered mandatory from the effective date of the original issue of this AD:
3.1. No later than within the next 100 flying hours or within one month (whichever limit is reached first):
a) Check the part number of HSI KI 525A installed on aircraft.
b) If the part number read is 066-3046-07, comply with the instructions given in paragraph 2.B of the
referenced ASB.
c) If the part number read is different from 066-3046-07, leave as is.
3.2. Before installing an HSI KI 525A, part number 066-3046-07, in place of an HSI KI 525A, part numbers
066-3046-00, -01, -04 or -05, on an aircraft, comply with the instructions defined in paragraph 2.B of
the referenced ASB.
n/DJ
D-2004-111R1
AIRWORTHINESS DIRECTIVE Distribution: Issue date: Page:
No F-2002-280-068 R1 A March 17, 2004 2/2
4. REFERENCE PUBLICATION:
EUROCOPTER AS 355 Alert Service Bulletin No. 34.00.09
(Any subsequent approved revision of this ASB is acceptable).
5. EFFECTIVE DATES :
Original issue : June 08, 2002
Revision 1 : March 27, 2004.
6. REMARK:
For any questions concerning the technical content of the requirements in this AD, please contact:
EUROCOPTER (STXI) – Aéroport de Marseille Provence, 13725 Marignane Cedex – France
Phone: +33 (0)4 42 85 97 97 – Fax: +33 (0)4 42 85 99 66
E-mail: Directive.technical-support@eurocopter.com
7. APPROVAL:
This Revision AD is approved under EASA reference No 2004-2116 dated March 09, 2004.
