Nachrichten für Luftfahrer 2007 Teil II (weicht ggf. von Druckversion ab)
D-2007-320 D-2007-320
EASA AIRWORTHINESS DIRECTIVE Compliance: Within 3 months after the effective date of this AD, it is mandatory to
adhere to the requirements of:
- AIRBUS A310 ALS Part 4 revision 01 for A310 aircraft,
- AIRBUS A300-600 ALS Part 4 revision 01 for A300-600 and A300-
AD No.: 2007-0092 600ST aircraft.
Note: For Operators who previously complied with the requirements of
cancelled Airworthiness Directives 85-033-067(B)R3, 2001-242(B) or F-
Date: 10 April 2007 2005-174 in regard to the life limitations/maintenance tasks, the last
accomplishment of each limitation/task must be retained as a starting
point for the accomplishment of each corresponding limitation/task interval
now introduced in the revision 01 of AIRBUS A310 or A300-600 ALS Part
No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the 4 documents.
requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry.
Type Approval Holder’s Name: Type/Model designation(s): Ref. Publications: AIRBUS A310 ALS Part 4 revision 01 approved on 21-Dec-2006;
AIRBUS A300-600 ALS Part 4 revision 01 approved on 21-Dec-2006, or
AIRBUS SAS A310, A300-600 and A300-600ST aircraft later approved revisions of these documents.
TCDS Number: DGAC France No 145; EASA A.014 Remarks: 1. If requested and appropriately substantiated the responsible EASA
manager for the related product has the authority to accept Alternative
Methods of Compliance (AMOCs) for this AD.
Foreign AD: Not applicable
2. This AD was posted on 14 February 2007 as PAD 06-246R1 for
Supersedure: DGAC AD 85-033-067(B)R3 ; DGAC AD 2001-242(B) ; DGAC AD F-2005-174 consultation until 07 March 2007. No comments were received during
(EASA approval No. 2005-6369) the consultation period.
3. Enquiries regarding this AD should be addressed to the AD Focal
Point – Certification Directorate, EASA; E-mail: ADs@easa.europa.eu
ATA 05 Ageing Systems Maintenance (ASM)
4. For any question concerning the technical content of the requirements
in this AD, please contact AIRBUS SAS – Airworthiness Office – EAZ
Fax: +33 5 61 93 37 44.
Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE)
Applicability: A310 aircraft, all certified models, all serial numbers.
A300-600 aircraft, all certified models, all serial numbers.
A300-600ST aircraft, all certified models, all serial numbers.
Reason:
The A310 Airworthiness Limitations Section (ALS) Part 4 and A300-600
ALS Part 4 have been issued to introduce the Airworthiness Limitations
applicable to A310, A300-600 and A300-600ST ageing aircraft systems in
the frame of aircraft extended Limit Of Validity (LOV). The first issue
(Revision 00) of these documents introduced Ageing Systems
Maintenance (ASM) limitations defined in accordance with a process
agreed between AIRBUS and the European Aviation Safety Agency
(EASA) by way of the equipment life extension study.
The Subpart 4-3(a) of the ALS Part 4 revision 01, related to the Trimmable
Horizontal Stabilizer Actuator, refers to maintenance tasks which satisfy
the intent of AD 2001-242(B). Therefore AD 2001-242(B) is cancelled.
The Subparts 4-2 and 4-3(a) of the A310 ALS Part 4 revision 01, related to
the Flap Screw Jack, refer to life limitations and maintenance tasks which
satisfy the intent of AD 85-033-067(B)R3. Therefore AD 85-033-067(B)R3
is cancelled.
The Subpart 4-3(b) of the A310 ALS Part 4 revision 01, related to the Flap
Transmission Shaft, refers to maintenance tasks which satisfy the intent of
CN F-2005-174. Therefore AD F-2005-174 is cancelled.
Effective Date: 24 April 2007
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D-2007-321
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2007-321
Luftfahrt-Bundesamt EASA AIRWORTHINESS DIRECTIVE
Datum der Bekanntgabe: 31.10.2007
Muster: LET AD der ausländischen Behörde:
L-13 "Blanik" EASA AD 2007-0212 vom 07.08.2007 AD No.: 2007-0212
Geräte-Nr.: Technische Mitteilungen des Herstellers:
247, EASA.A.024 Aircraft Industries a.s Documentation Bulletin No. L13/009d
Aircraft Industries a.s Documentation Bulletin No. L13/010d
Aircraft Industries a.s Documentation Bulletin No. L13/011d
Aircraft Industries a.s Mandatory Bulletin No. L13/105a Date: 07 August 2007
Betroffenes Luftfahrtgerät: No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the
requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry.
LET
L-13 "Blanik" Type Approval Holder’s Name : Type/Model designation(s) :
- Baureihen: L13 und L13A Blanik AIRCRAFT INDUSTRIES a.s. L13 “BLANÍK” sailplanes
- Werk-Nrn.: alle TCDS Number: EASA A.024
Betrifft: Foreign AD: Not applicable
Flugsteuerung (''Flight Controls – Control Sticks and Bridge – Inspection/Replacement'')
Supersedure: Not applicable
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA-AD und der
oben 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 durchgeführt werden. Alle ATA 27 Flight Controls – Control Sticks and Bridge – Inspection/Replacement
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen
Zustimmung durch das Luftfahrt-Bundesamt.
Manufacturer(s): Aircraft Industries a.s.; Strojírny první ptiletky n.p.; LET n.p.; and LET a.s.
Fristen:
Alle anzuwendenden Fristen sind der o. g. EASA-AD zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der o. g. EASA-AD. Applicability: L13 and L13A BLANÍK sailplanes, all serial numbers
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
Reason: This Airworthiness Directive (AD) is prompted by the discovery of cracks on L13
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es BLANIK sailplanes in zones where the forward and aft control sticks are attached to
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen. the connecting rod, designated as “control bridge” in the relevant Illustrated Parts
Catalogues (IPC). If left uncorrected, cracks could propagate and lead to failure of the
Rechtsbehelfsbelehrung: connecting rod with subsequent loss of control of the sailplane.
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. For the reasons described above, this AD requires an inspection of the control bridge
to detect cracks and replacement, if necessary. In addition, this AD requires an
LTAs werden auch im Internet unter http://www.lba.de publiziert
*** update of the aircraft Maintenance Manual (MM) to incorporate repetitive inspections
of the control bridge.
Effective Date: 21 August 2007
Compliance: Required as indicated, at the next scheduled “A” Type maintenance inspection or
within the next 3 months after the effective date of this AD, whichever occurs first.
(1) Inspect the control bridge for cracks in areas of juncture with the two control sticks
as instructed in paragraph A. of Aircraft Industries a.s Mandatory Bulletin (MB)
No. L13/105a initial issue or later approved revision.
If any crack is found, before further flight, replace the control bridge as indicated in
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D-2007-321
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2007-322
aforesaid Aircraft Industries MB;
(2) Update the sailplane Maintenance Manual to include the repetitive inspection of Luftfahrt-Bundesamt
the control bridge in accordance with instructions of Aircraft Industries
Datum der Bekanntgabe: 31.10.2007
Documentation Bulletin (DB) No.L13/009d for L13 sailplanes, and DB Muster: Eurocopter AD der ausländischen Behörde:
No.L13/010d for L13 sailplanes maintained without overhauls, and DB SA 365 EASA AD 2007-0220 vom 13.08.2007
No.L13/011d for L13A sailplanes; and
Geräte-Nr.: Technische Mitteilungen des Herstellers:
Modify the aircraft maintenance programme accordingly.
3052, DGAC TCDS 159 Eurocopter AS 365 Alert Service Bulletin No. 01.00.59 vom
21.06.2007
Ref. Aircraft Industries a.s Mandatory Bulletin No. L13/105a initial issue or later approved
Publications: revisions;
Betroffenes Luftfahrtgerät:
Aircraft Industries a.s Documentation Bulletins No.L13/009d, L13/010d and L13/011d.
Eurocopter
Remarks : 1. If requested and appropriately substantiated the responsible EASA manager for SA 365
the related product has the authority to accept Alternative Methods of Compliance
(AMOCs) for this AD. - Baureihen: SA 365 N1, AS 365 N2 und AS 365 N3
2. This AD was posted for consultation on 10 July 2007 as PAD 07-112 until
24 July 2007. No comments were received during the consultation period. - Werk-Nrn.: alle, gemäß den Angaben der EASA-AD
3. Enquiries regarding this AD should be referred to the AD Focal Point -
Certification Directorate, EASA. E-mail: ADs@easa.europa.eu . Betrifft:
Heckrotor / Heckrotorantrieb (''Tail Rotor Drive – Tail Rotor Blade Pitch Control Shafts –
4. For any question concerning the technical content of the requirements in this AD, Identification/Replacement'')
please contact:
AIRCRAFT INDUSTRIES a.s.,
Na Záhonech 1177, 686 04 Kunovice, CZECH REPUBLIC
Maßnahmen:
Phone: +420 572 817 660 Fax: +420 572 816 112; Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA-AD und der
E-mail: ots@let.cz oben 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 durchgeführt werden. Alle
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen
Zustimmung durch das Luftfahrt-Bundesamt.
Fristen:
Alle anzuwendenden Fristen sind der o. g. EASA-AD zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der o. g. EASA-AD.
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
***
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D-2007-322 D-2007-322
EASA AIRWORTHINESS DIRECTIVE Effective Date: 27 August 2007
Compliance: (1) Not later than 31 December 2007, replace all P/N 365A33.6161.20 and
365A33.6161.21 aluminium Tail Rotor Blade Pitch Control Shafts with a
AD No : 2007-0220 steel P/N 365A33.6214.20 shaft in accordance with Eurocopter AS365 Alert
Service Bulletin (ASB) 01.00.59;
(2) After 31 December 2007, no person may install P/N 365A33.6161.20 and
365A33.6161.21 aluminium Tail Rotor Blade Pitch Control Shafts on any
Date: 13 August 2007 helicopter. All units held as spares must be scrapped or returned to
Eurocopter for disposal.
Ref. Publications: EUROCOPTER AS365 Alert Service Bulletin (ASB) 01.00.59 dated 21 June
No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the
requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry. 2007 or later approved revisions.
Type Approval Holder’s Name : Type/Model designation(s) : Remarks : 1. If requested and appropriately substantiated the responsible EASA manager
for the related product has the authority to accept Alternative Methods of
EUROCOPTER SA 365 N and AS 365 N helicopters Compliance (AMOCs) for this AD.
2. This AD was posted for consultation on 11 July 2007 as PAD 07-103 until
TCDS Number: France No.159 08 August 2007. No comments were received during the consultation period.
3. Enquiries regarding this AD should be referred to the AD Focal Point -
Foreign AD: Not applicable Certification Directorate, EASA. E-mail: ADs@easa.europa.eu .
4. For any question concerning the technical content of the requirements in this
Supersedure: None AD, please contact:
EUROCOPTER (STDI) - Aéroport de Marseille Provence 13725 Marignane
Cedex – France; Telephone: 33 (0) 4 42 85 97 97 - Fax: 33 (0) 4 42 85 99 66.
E-mail: Directive.technical-support@eurocopter.com.
Tail Rotor Drive – Tail Rotor Blade Pitch Control Shafts –
ATA 65
Identification/Replacement
Manufacturer(s): EUROCOPTER (Formerly EUROCOPTER FRANCE, AEROSPATIALE).
Applicability: SA 365 N1, AS 365 N2 and AS 365 N3 helicopters, all serial numbers, equipped
with an aluminium Tail Rotor Blade Pitch Control Shaft with Part Number (P/N)
365A33.6161.20 or 365A33.6161.21
Reason: During a recent incident, the pilot of a Model AS 365 N2 helicopter noticed loss
of control of the Tail Rotor. A decision was made to continue the flight to the
nearest airport and an uneventful run-on landing was made.
Subsequent investigation showed that the Tail Rotor Blade Pitch Control Shaft
P/N 365A33.6161.21 had broken. This failure occurred in the main section of
shaft sliding area, which appeared to have been damaged by peening. For that
reason the origin of the crack, which developed under fatigue loading, could not
be determined. Most likely, accidental damage (e.g. shock impact) is thought to
have caused the initiation of a crack in the hard tungsten-carbide deposit on the
shaft. Damage of this kind cannot be detected through normal inspection
methods. This condition, if not corrected, could lead to further cases of control
shaft failure and consequent loss of tail rotor control
EUROCOPTER has developed a steel control shaft, P/N 365A33.6214.20, that is
less sensitive to shock-induced damage. For this reason, the present AD
requires replacement of the affected aluminium control shafts and the withdrawal
from service of all remaining spares.
1/2 2/2
D-2007-323
Lufttüchtigkeitsanweisung Transport Transports TP 7245E
Canada Canada
LTA-Nr.: D-2007-323 No.
1/1
CF-2007-11
Issue Date
Luftfahrt-Bundesamt 09 August 2007
Datum der Bekanntgabe: 02.11.2007
Muster: Bombardier / De Havilland
DHC-8
AD der ausländischen Behörde:
TC AD CF-2007-11 vom 09.08.2007
AIRWORTHINESS DIRECTIVE
The following airworthiness directive (AD) may be applicable to an aircraft which our records indicate is registered in your name. ADs are issued pursuant to Canadian Aviation
Regulation (CAR) 593. Pursuant to CAR 605.84 and the further details of CAR Standard 625, Appendix H, the continuing airworthiness of a Canadian registered aircraft is
contingent upon compliance with all applicable ADs. Failure to comply with the requirements of an AD may invalidate the flight authorization of the aircraft. Alternative means of
compliance shall be applied for in accordance with CAR 605.84 and the above-referenced Standard.
Geräte-Nr.: Technische Mitteilungen des Herstellers: This AD has been issued by the Continuing Airworthiness Division (AARDG), Aircraft Certification Branch, Transport Canada, Ottawa, telephone 613 952-4357.
2848, EASA.IM.A.191 Bombardier Service Bulletin 8-33-53 Revision A vom 14.03.2007
Bombardier Service Bulletin 8-33-53 vom 01.12.2006 Number: CF-2007-11
Bombardier Service Bulletin 84-33-10 Revision A vom 14.03.2007
Bombardier Service Bulletin 84-33-10 vom 01.12.2006 Subject: Flight Compartment - Utility and Observer Lights
Effective: 31 August 2007
Betroffenes Luftfahrtgerät:
Applicability: Bombardier Inc. DHC-8 Aircraft Models 102, 103, 106, 201, 202, 301, 311, 314 and 315,
Bombardier / De Havilland Serial Numbers 003 through 639.
DHC-8
Bombardier Inc. DHC-8 Aircraft Models 400, 401 and 402, Serial Numbers 4003, 4004,
- Baureihen: DHC-8-102, -103, -106, -201, -202, -301, -311, -314 und 315 4006 and 4008 through 4149.
- Werk-Nrn.: 003 bis 639
Compliance: Within 18 months after the effective date of this directive, unless already accomplished.
Background: Several cases have been reported where the pilot, co-pilot or observer utility light system has
DHC-8-400, -401 und -402 failed, resulting in a burning smell within the cockpit. An investigation has revealed that, due
- Werk-Nrn.: 4003, 4004, 4006 und 4008 bis 4149 to the orientation and location of the carbon molded potentiometers used to control the
intensity of the light, the potentiometers can fail and overheat in such a way that burning of
- Werk-Nrn.: siehe Angaben unter ''Baureihen'' the ceiling panel and the associated insulation blanket could occur. This could lead to the
presence of smoke in the cockpit, requiring that the pilots carry out the appropriate
Betrifft: emergency procedure.
Flight Compartment / Beleuchtungsanlage (''Utility and Observer Lights'')
Corrective A. Applicable to DHC-8 Aircraft Models 102, 103, 106, 201, 202, 301, 311, 314 and 315
Actions: 1. Install Modsum 8Q101603 to replace the affected carbon molded resistive element
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten AD der potentiometers with wire-wound type potentiometers, for both the pilot and co-pilot
ausländischen Behörde und der oben genannten Technischen Mitteilung des Herstellers zu entnehmen. utility lights. Bombardier Service Bulletin (SB) 8-33-53, original issue dated 1
December 2006, Revision A dated 14 March 2007, or later revisions approved by
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig the Chief, Continuing Airworthiness, Transport Canada, provide instructions for
und innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle incorporating Modsum 8Q101603.
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen
Zustimmung durch das Luftfahrt-Bundesamt. B. Applicable to DHC-8 Aircraft Models 400, 401 and 402
1. Install Modsum 4-126381 to replace the affected carbon molded resistive element
Fristen: potentiometers with wire-wound type potentiometers, for the pilot, co-pilot and
Alle anzuwendenden Fristen sind der o. g. AD der ausländischen Behörde zu entnehmen. observer utility lights. Bombardier Service Bulletin (SB) 84-33-10, original issue
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der o. g. AD der dated 1 December 2006, Revision A dated 14 March 2007, or later revisions
ausländischen Behörde. approved by the Chief, Continuing Airworthiness, Transport Canada, provide
instructions for incorporating Modsum 4-126381.
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen Authorization: For Minister of Transport, Infrastructure and Communities
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:
B. Goyaniuk
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder Chief, Continuing Airworthiness
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
Contact: Mr. Anthony Wan, Continuing Airworthiness, Ottawa, telephone (613) 952-4410,
LTAs werden auch im Internet unter http://www.lba.de publiziert facsimile (613) 996-9178 or e-mail wana@tc.gc.ca or any Transport Canada Centre.
***
Pursuant to CAR 202.51 the registered owner of a Canadian aircraft shall, within seven days, notify the Minister
in writing of any change of his or her name or address.
To request a change of address, contact the Civil Aviation Communications Centre (AARC)
at Place de Ville, Ottawa, Ontario K1A 0N8, or 1-800-305-2059,
or www.tc.gc.ca/civilaviation/communications/centre/ address.asp
24-0022 (01-2005)
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D-2007-324
Lufttüchtigkeitsanweisung AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2007-324 FAA
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/
Luftfahrt-Bundesamt www.gpoaccess.gov/fr/advanced.html
Datum der Bekanntgabe: 02.11.2007
Muster: Sikorsky AD der ausländischen Behörde: 2007-17-05 Sikorsky Aircraft Corporation: Amendment 39-15163. Docket No. FAA-2007-28971;
S-92A FAA AD 2007-17-05 Amdt. 39-15163
Directorate Identifier 2007-SW-32-AD.
Geräte-Nr.: Technische Mitteilungen des Herstellers:
EASA.IM.R.001 Sikorsky Alert Service Bulletin No. 92-64-002 vom 03.08.2007 Applicability
Betroffenes Luftfahrtgerät: Model S-92A helicopter, with a tail rotor pitch change shaft and bearing assembly (shaft and
bearing assembly) part number 92358-06303-041, installed, certificated in any category.
Sikorsky
S-92A
Compliance
- Baureihen: S-92A
Required as indicated, unless accomplished previously.
- Werk-Nrn.: alle, gemäß den Angaben der AD der ausländischen Behörde To prevent failure of a shaft and bearing assembly, loss of tail rotor pitch and yaw control, and
subsequent loss of control of a helicopter, do the following:
Betrifft:
Heckrotor (''failure of a shaft and bearing assembly'')
(a) Within 20 hours time-in-service (TIS), borescope inspect as follows:
(1) Inspect each affected shaft and bearing assembly at tail rotor side by following the
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten AD der Accomplishment Instructions, paragraphs 3.A.(1) through (7) and Figure 4 of Sikorsky Aircraft
ausländischen Behörde und der oben genannten Technischen Mitteilung des Herstellers zu entnehmen. Corporation Alert Service Bulletin No. 92-64-002, dated August 3, 2007 (ASB). If the shaft bearing
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig fails the inspection, replace the shaft and bearing assembly before further flight.
und innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle (2) Inspect each shaft and bearing assembly on the servo side through the oil filler cap by
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen
following the Accomplishment Instructions, paragraphs B.(1) through (9) and Figures 2 and 3, of the
Zustimmung durch das Luftfahrt-Bundesamt.
ASB. If the shaft bearing fails the inspection, replace the shaft and bearing assembly before further
Fristen: flight.
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 Note: Maintenance Manual SA S92A-ANM-000 pertains to the subject of this AD.
ausländischen Behörde.
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
(b) Between 10 and 15 hours TIS after installing a shaft and bearing assembly, borescope inspect
nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der it by following paragraph (a) of this AD.
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.
(c) To request a different method of compliance or a different compliance time for this AD,
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
follow the procedures in 14 CFR 39.19. Contact the Manager, Boston Aircraft Certification Office,
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. FAA, ATTN: Wayne Gaulzetti, Aviation Safety Engineer, 12 New England Executive Park,
LTAs werden auch im Internet unter http://www.lba.de publiziert
Burlington, MA 01803, telephone (781) 238-7156, fax (781) 238-7170, for information about
*** previously approved alternative methods of compliance.
(d) The inspections of the shaft and bearing assembly shall be done by following Sikorsky Alert
Service Bulletin No. 92-64-002, dated August 3, 2007. The Director of the Federal Register approved
this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be
obtained from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support,
mailstop s581a, 6900 Main Street, Stratford, Connecticut, phone (203) 383-4866, e-mail address
tsslibrary@sikorsky.com. Copies may be inspected at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas or at the National Archives
and Records Administration (NARA). For information on the availability of this material at NARA,
5
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D-2007-324
call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ Lufttüchtigkeitsanweisung
ibr_locations.html. LTA-Nr.: D-2007-325
(e) This amendment becomes effective on August 21, 2007. Luftfahrt-Bundesamt
Datum der Bekanntgabe: 02.11.2007
Issued in Fort Worth, Texas, on August 9, 2007. Muster: Bombardier Inc. AD der ausländischen Behörde:
Mark R. Schilling, CL-600 TC AD CF-2007-23 vom 18.10.2007
Manager, Rotorcraft Directorate, Aircraft Certification Service. Geräte-Nr.: Technische Mitteilungen des Herstellers:
[FR Doc. E7-15980 Filed 8-20-07; 8:45 am] 2854, EASA.IM.A.023 Bombardier Service Bulletin 601R-28-054 Revision A vom
07.08.2006
Betroffenes Luftfahrtgerät:
Bombardier Inc.
CL-600
- Baureihen: CL-600-2B19
- Werk-Nrn.: 7003 bis 7067 und 7069 bis 7981
Betrifft:
KRAFTSTOFFANLAGE (ATA: 28): Kraftstoffleitungen und Verbindungsbauteile in den Kraftstofftanks -
Elektrische Masseverbindung / Blitzschutz (Kraftstofftanksicherheit / Fuel Tank Safety)
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten TC Airworthiness
Directive (AD) und den genannten technischen Mitteilungen 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 durchgeführt werden. Alle Abweichungen von
den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das
Luftfahrt-Bundesamt.
Fristen:
Alle anzuwendenden Fristen sind der oben genannten TC Airworthiness Directive (AD) zu entnehmen. Die
Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten TC
Airworthiness Directive (AD).
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
TC AD CF-2007-23 vom 18.10.2007
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
***
6
Aktenzeichen: (01)T232-502.1/D-2007-325 Seite 1 von 1
Transport Transports TP 7245E Lufttüchtigkeitsanweisung
Canada Canada No.
CF-2007-23 1/1 LTA-Nr.: D-2007-326
Issue Date
18 October 2007 Luftfahrt-Bundesamt
Datum der Bekanntgabe: 05.11.2007
AIRWORTHINESS DIRECTIVE Muster: Teledyne Continental
TSIO-520
AD der ausländischen Behörde:
FAA AD 2007-16-10 Amdt. 39-15149
The following airworthiness directive (AD) may be applicable to an aircraft which our records indicate is registered in your name. ADs are issued pursuant to Canadian Aviation
Regulation (CAR) 593. Pursuant to CAR 605.84 and the further details of CAR Standard 625, Appendix H, the continuing airworthiness of a Canadian registered aircraft is
contingent upon compliance with all applicable ADs. Failure to comply with the requirements of an AD may invalidate the flight authorization of the aircraft. Alternative means of
compliance shall be applied for in accordance with CAR 605.84 and the above-referenced Standard.
TSIO-550
This AD has been issued by the Continuing Airworthiness Division (AARDG), Aircraft Certification Branch, Transport Canada, Ottawa, telephone 613 952-4357.
Geräte-Nr.: Technische Mitteilungen des Herstellers:
Number: CF-2007-23 4587, 4619 Cirrus Service Advisory SA 07-14 R1 vom 24.07.2007
Kelly Aerospace Power Systems Service Bulletin No. 026
Subject: Fuel System Safety - Insufficient Electrical Bonding Between Fuel Tubes and Revision B vom 27.07.2007
Insufficient Lightning Current Capability of Fuel Tube Couplings Kelly Aerospace Power Systems Service Bulletin No. 027 vom
25.07.2007
Effective: 1 November 2007 Teledyne Continental Aircraft Engine Mandatory Service Bulletin
(MSB) MSB07-4 vom 30.07.2007
Applicability: Bombardier Inc. Model CL-600-2B19 aircraft, serial numbers 7003 through 7067, and
7069 through 7981. Betroffenes Luftfahrtgerät:
Compliance: Compliance is required as indicated unless already accomplished. Teledyne Continental
TSIO-520, TSIO-550
Background: Bombardier Aerospace has completed a system safety review of the CL-600-2B19
aircraft fuel system against new fuel tank safety standards, introduced in Chapter 525 of - Baureihen: TSIO-520-BE
the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The IO-550-N
identified non-compliances were assessed using Transport Canada Policy Letter TSIO-550-A, TSIO-550-B, TSIO-550-C, TSIO-550-E, TSIO-550-G
No. 525-001 to determine if mandatory corrective action is required.
- Werk-Nrn.: TSIO-520-BE, TSIO- 550-A, TSIO-550-B, TSIO-550-C, TSIO-550-E und TSIO-550-G
The assessment and lightning tests showed that certain fuel tube self-bonded couplings ausgerüstet mit Kelly Aerospace Power Systems Turbolader, TCM-Teilenummer
do not provide sufficient lightning current capability. The assessment also showed that (P/N) 646677, mit bestimmten Seriennummern (S/N), installiert ab dem 20.03.2007
single failure of the integral bonding wire of the self-bonded couplings or excessive axial und
clearance at the reducer ferrules of certain self-bonded couplings could affect electrical TCM IO-550-N modifiziert nach dem Engine Technologies Incorporated FAA Supplemental
bonding between fuel tubes. Type Certificate (STC) SE10589SC zur Installation des Turboladers P/N 466304-0003,
mit bestimmten Seriennummern (S/N), installiert ab dem 20.03.2007.
Insufficient electrical bonding between fuel tubes or insufficient current capability of fuel
tube couplings, if not corrected, could result in arcing and potential ignition source inside Weitere Hinweise zu betroffenen Turbolader-Seriennummern können den genannten
the fuel tank during lightning strikes and consequent fuel tank explosion. To correct the Service Bulletins der Hersteller TCM , Kelly Aerospace Power Systems und Cirrus
unsafe condition, this directive mandates the replacement of certain fuel tube couplings entnommen werden.
with redesigned couplings.
Corrective Within 5000 hours air time after the effective date of this directive, replace fuel tube
Betrifft:
couplings inside the wing and centre fuel tanks with redesigned couplings, according to Möglicher Verlust der Triebwerksleistung, starke Ölleckagen am Turbolader und Abgase im Cockpit
Action:
the Accomplishment Instructions of Bombardier Service Bulletin (SB) 601R-28-054, durch Loslösung des Turbinenrades innerhalb des Turboladers aufgrund von Herstellungsfehlern.
Revision A, dated 7 August 2006, or later revisions approved by the Chief, Continuing
Airworthiness, Transport Canada. Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA
Airworthiness Directive und den genannten technischen Mitteilungen der Hersteller zu entnehmen.
Authorization: For Minister of Transport, Infrastructure & Communities Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
vollständig und innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchge-
führt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung
bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
B. Goyaniuk
Chief, Continuing Airworthiness Fristen:
Alle anzuwendenden Fristen sind der oben genannten FAA Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
Contact: Mr. Philip Tang, Continuing Airworthiness, Ottawa, telephone (613) 952-4365, facsimile FAA Airworthiness Directive.
(613) 996-9178 or e-mail tangp@tc.gc.ca or any Transport Canada Centre.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
Pursuant to CAR 202.51 the registered owner of a Canadian aircraft shall, within seven days, notify the Minister
in writing of any change of his or her name or address. FAA AD 2007-16-10 Amdt. 39-15149
To request a change of address, contact the Civil Aviation Communications Centre (AARC)
at Place de Ville, Ottawa, Ontario K1A 0N8, or 1-800-305-2059,
or www.tc.gc.ca/civilaviation/communications/centre/ address.asp
24-0022 (01-2005)
Aktenzeichen: (10)T23-502.1/D-2007-326 Seite 1 von 2
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 [Federal Register: August 8, 2007 (Volume 72, Number 152)]
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es [Rules and Regulations]
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
[Page 44370-44371]
Rechtsbehelfsbelehrung: From the Federal Register Online via GPO Access [wais.access.gpo.gov]
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. [DOCID:fr08au07-3]
LTAs werden auch im Internet unter http://www.lba.de publiziert
*** ––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28863; Directorate Identifier 2007-NE-33-AD; Amendment 39-15149;
AD 2007-16-10]
RIN 2120-AA64
Airworthiness Directives; Teledyne Continental Motors Reciprocating (TCM) Engine Models
IO-550-N, TSIO-520-BE, TSIO-550-A, TSIO-550-B, TSIO-550-C, TSIO-550-E, and TSIO-550-
G
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
ACTION: Final rule; request for comments.
––––––––––––––––––––––––––––––––––
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for TCM IO-550-N, TSIO-
520-BE, TSIO-550-A, TSIO-550-B, TSIO-550-C, TSIO-550-E, and TSIO-550-G reciprocating
engines. This AD requires removing before further flight, certain Kelly Aerospace Power Systems
turbochargers, part number (P/N) 466304-0003, listed by serial number in this AD. This AD results
from four incidents of the turbine rotor separating from the shaft of the turbocharger. We are issuing
this AD to prevent the turbine rotor from separating from the shaft of the turbocharger due to a
machining defect in the turbocharger compressor. This condition could result in full engine power
loss, loss of engine lubricant, or smoke in the airplane cabin.
DATES: This AD becomes effective August 23, 2007. The Director of the Federal Register approved
the incorporation by reference of certain publications listed in the regulations as of August 23, 2007.
We must receive any comments on this AD by October 9, 2007.
ADDRESSES: Use one of the following addresses to comment on this AD:
• DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your
comments electronically.
• Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the
instructions for sending your comments electronically.
• Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground
Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.
• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
• Fax: (202) 493-2251.
1
Aktenzeichen: (10)T23-502.1/D-2007-326 Seite 2 von 2
Contact Kelly Aerospace Power Systems, 2900 Selma Highway, Montgomery, AL 36108; anyone can find and read the comments in any of our dockets, including the name of the individual
telephone (334) 386-5400; fax (334) 386-5450; http://www.kellyaerospace.com for the service who sent the comment (or signed the comment on behalf of an association, business, labor union,
information identified in this AD. etc). You may review the DOT's complete Privacy Act Statement in the Federal Register published
on April 11, 2000 (65 FR 19477-78) or you may visit http://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Kevin Brane, Aerospace Engineer, Atlanta
Aircraft Certification Office, FAA, Small Airplane Directorate, One Crown Center, 1895 Phoenix Examining the AD Docket
Blvd., Suite 450, Atlanta, GA 30349; e-mail: kevin.brane@faa.gov; telephone (770) 703-6063; fax
(770) 703-6097. You may examine the AD docket on the Internet at http://dms.dot.gov; or in person at the Docket
Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The
SUPPLEMENTARY INFORMATION: On July 16, 2007, Kelly Aerospace Power Systems AD docket contains this AD, the regulatory evaluation, any comments received, and other
informed us that there were potential nonconforming turbochargers, P/N 466304-0003 that might information. The street address for the Docket Operations office (telephone (800) 647-5527) is
have a machining defect in the compressors of the turbochargers. A machining defect in the provided in the ADDRESSES section. Comments will be available in the AD docket shortly after
turbocharger compressor leads to a condition where the center bore of the compressor is not receipt.
perpendicular to the backface of the compressor. The machining defect leads to abnormal
turbocharger rotor vibration which results in abnormal wear characteristics. The wear could result in Authority for this Rulemaking
the turbocharger rotor separating from the shaft. This condition, if not corrected, could result in full
engine power loss, loss of engine lubricant, or smoke in the airplane cabin. Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
Relevant Service Information Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III,
We have reviewed and approved the technical contents of Kelly Aerospace Power Systems Section 44701, ''General requirements.'' Under that section, Congress charges the FAA with
Service Bulletins (SBs) No. 026, Revision B, dated July 27, 2007, and No. 027, dated July 25, 2007. promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
Those SBs list affected turbochargers by SN, and describe procedures for visually inspecting the methods, and procedures the Administrator finds necessary for safety in air commerce. This
turbocharger. 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.
FAA's Determination and Requirements of this AD
Regulatory Findings
The unsafe condition described previously is likely to exist or develop on other engines of the
same type design. For that reason, we are issuing this AD to prevent the turbine rotor from separating We have determined that this AD will not have federalism implications under Executive Order
from the shaft of the turbocharger due to a machining defect in the turbocharger compressor. This 13132. This AD will not have a substantial direct effect on the States, on the relationship between the
condition could result in full engine power loss, loss of engine lubricant, or smoke in the airplane national Government and the States, or on the distribution of power and responsibilities among the
cabin. This AD requires replacing certain turbochargers before further flight. You must use the various levels of government.
service information described previously to perform the actions required by this AD. For the reasons discussed above, I certify that this AD:
1. Is not a ''significant regulatory action'' under Executive Order 12866;
FAA's Determination of the Effective Date 2. Is not a ''significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979); and
Since an unsafe condition exists that requires the immediate adoption of this AD, we have found 3. Will not have a significant economic impact, positive or negative, on a substantial number of
that notice and opportunity for public comment before issuing this AD are impracticable, and that small entities under the criteria of the Regulatory Flexibility Act.
good cause exists for making this amendment effective in less than 30 days. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket.
You may get a copy of this summary at the address listed under ADDRESSES.
Comments Invited
List of Subjects in 14 CFR Part 39
This AD is a final rule that involves requirements affecting flight safety and was not preceded by
notice and an opportunity for public comment; however, we invite you to send us any written relevant Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
data, views, or arguments regarding this AD. Send your comments to an address listed under
ADDRESSES. Include ''AD Docket No. FAA-2007-28863; Directorate Identifier 2007-NE-33-AD'' Adoption of the Amendment
in the subject line of your comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might suggest a need to modify it. Under the authority delegated to me by the Administrator, the Federal Aviation Administration
We will post all comments we receive, without change, to http://dms.dot.gov, including any amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
personal information you provide. We will also post a report summarizing each substantive verbal
contact with FAA personnel concerning this AD. Using the search function of the DMS Web site,
2 3
