Nachrichten für Luftfahrer 2007 Teil II (weicht ggf. von Druckversion ab)
PART 39–AIRWORTHINESS DIRECTIVES AIRWORTHINESS DIRECTIVE
FAA
1. The authority citation for part 39 continues to read as follows: Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html
Authority: 49 U.S.C. 106(g), 40113, 44701.
2007-16-10 Teledyne Continental Motors: Amendment 39-15149. Docket No. FAA-2007-28863;
§ 39.13 [Amended] Directorate Identifier 2007-NE-33-AD.
2. The FAA amends § 39.13 by adding the following new airworthiness directive: Effective Date
(a) This airworthiness directive (AD) becomes effective August 23, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to:
(1) Teledyne Continental Motors (TCM) models TSIO-520-BE, TSIO-550-A, TSIO-550-B,
TSIO-550-C, TSIO-550-E, and TSIO-550-G reciprocating engines with a Kelly Aerospace Power
Systems turbocharger, TCM part number (P/N) 646677, with certain serial numbers (SNs), installed
on or after March 20, 2007. These engines are installed on, but not limited to, Adam Aircraft A500,
Columbia Aircraft Manufacturing LC41-550FG, Mooney Airplane Company M20TN (Acclaim), and
Piper Aircraft Incorporated PA-46-310P (Malibu) airplanes.
(2) TCM IO-550-N reciprocating engines modified to Engine Technologies Incorporated
supplemental type certificate (STC) SE10589SC to install turbocharger, P/N 466304-0003, with
certain SNs, installed on or after March 20, 2007. These engines are installed on, but not limited to,
Cirrus Design Corporation Aircraft Model SR22 modified to Engine Technologies Incorporated STC
SA10588SC.
Unsafe Condition
(d) 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.
Compliance
(e) You are responsible for having the actions required by this AD performed before further
flight unless the actions have already been done.
(f) If your engine has a turbocharger that was installed before March 20, 2007, no further action
is required.
4 5
Engines Modified to Engine Technologies Incorporated STC SE10589SC Issued in Burlington, Massachusetts, on August 1, 2007.
Peter A. White,
(g) Before further flight, for engines modified to Engine Technologies Incorporated STC Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
SE10589SC on or after March 20, 2007, with a turbocharger that has a SN listed in Kelly Aerospace [FR Doc. 07-3840 Filed 8-6-07; 11:44 am]
Service Bulletin (SB) No. 026, Revision B, dated July 27, 2007, replace the turbocharger.
TCM Engines with Turbocharger TCM P/N 646677
(h) Before further flight, for engines with a Kelly Aerospace Power Systems turbocharger, TCM
P/N 646677 installed on or after March 20, 2007, with a turbocharger SN listed in Kelly Aerospace
SB No. 027, dated July 25, 2007, replace the turbocharger.
Alternative Methods of Compliance
(i) The Manager, Atlanta Aircraft Certification Office, has the authority to approve alternative
methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19.
Special Flight Permits
(j) We are limiting the special flight permits for this AD by allowing a special flight permit only
after visually inspecting the turbocharger using the procedures specified in the Visual Inspection
sections of Kelly Aerospace Power Systems SB No. 026, Revision B, dated July 27, 2007, and SB
No. 027, dated July 25, 2007.
Related Information
(k) Teledyne Continental Aircraft Engine Mandatory Service Bulletin (MSB) MSB07-4, dated
July 30, 2007, contains additional information on replacing turbochargers on TCM engines and
Cirrus Service Advisory SA 07-14 R1, dated July 24, 2007, contains additional information on
replacing turbochargers on Cirrus Design Corporation Aircraft Model SR22 modified to Engine
Technologies Incorporated STC SA10588SC.
(l) Contact Kevin Brane, Aerospace Engineer, Atlanta Aircraft Certification Office, FAA, Small
Airplane Directorate, One Crown Center, 1895 Phoenix Blvd., Suite 450, Atlanta, GA 30349; e-mail:
kevin.brane@faa.gov; telephone (770) 703-6063; fax (770) 703-6097,
for more information about this AD.
Material Incorporated by Reference
(m) You must use Kelly Aerospace Power Systems Service Bulletins No. 026, Revision B, dated
July 27, 2007, and No. 027, dated July 25, 2007, to determine if you have an affected turbocharger
installed. The Director of the Federal Register approved the incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Kelly Aerospace Power
Systems, 2900 Selma Highway, Montgomery, AL 36108; telephone (334) 386-5400; fax (334) 386-
5450; http://www.kellyaerospace.com, for a copy of this service information. You may review copies
at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the
National Archives and Records Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-
locations.html.
6 7
Lufttüchtigkeitsanweisung AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2007-327 FAA
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/
Luftfahrt-Bundesamt www.gpoaccess.gov/fr/advanced.html
Datum der Bekanntgabe: 05.11.2007
Muster: Boeing AD der ausländischen Behörde: 2007-20-01 Boeing: Amendment 39-15211. Docket No. FAA-2007-28349; Directorate Identifier
BOEING 747 FAA AD 2007-20-01 Amdt. 3915211
2007-NM-025-AD.
Geräte-Nr.: Technische Mitteilungen des Herstellers:
2832 Boeing Service Bulletin 747-57-2326 vom 04.01.2007 Effective Date
Boeing Service Bulletin 747-57-2327 Revision 1 vom 10.07.2006
(a) This AD becomes effective October 31, 2007.
Betroffenes Luftfahrtgerät:
Boeing
Affected ADs
BOEING 747
(b) None.
- Baureihen: 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F
und 747SP Applicability
- Werk-Nrn.: Gemäß Boeing Service Bulletin 747-57-2327 Revision 1 (c) This AD applies to Boeing Model 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300,
und Boeing Service Bulletin 747-57-2326 747-400, 747-400D, 747-400F, and 747SP series airplanes, certificated in any category; as identified
in Boeing Special Attention Service Bulletin 747-57-2327, Revision 1, dated July 10, 2006; and
Boeing Special Attention Service Bulletin 747-57-2326, dated January 4, 2007.
Betrifft:
TRAGFLÄCHEN (ATA: 57): Fastener-Befestigungen an den Kraftstofftankwänden und Schellen der
Unsafe Condition
elektrischen Kabelbündel - Änderung / Abdichtung (Kraftstofftanksicherheit / Fuel Tank Safety)
Maßnahmen: (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA Airworthiness AD to prevent arcing inside the fuel tanks in the event of a lightning strike or high-powered short
Directive (AD) und den genannten technischen Mitteilungen des Herstellers zu entnehmen. Alle erforderlichen circuit, which could result in a fuel tank explosion or fire.
Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und innerhalb der
vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle Abweichungen von Compliance
den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das
Luftfahrt-Bundesamt.
(e) You are responsible for having the actions required by this AD performed within the
Fristen: compliance times specified, unless the actions have already been done.
Alle anzuwendenden Fristen sind der oben genannten FAA Airworthiness Directive (AD) zu entnehmen. Die
Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten FAA Change and Seal
Airworthiness Directive (AD).
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
(f) Within 60 months after the effective date of this AD, do the actions required by paragraphs
FAA AD 2007-20-01 Amdt. 3915211 (f)(1) and (f)(2) of this AD.
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen (1) Reconfigure the wire bundle clamps and seal the ends of certain fasteners inside the auxiliary
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 fuel tank, main fuel tanks, and surge fuel tanks, in accordance with the Accomplishment Instructions
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen. of Boeing Special Attention Service Bulletin 747-57-2327, Revision 1, dated July 10, 2006.
Rechtsbehelfsbelehrung: (2) Seal the ends of certain fasteners inside the main fuel tanks, in accordance with the
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder Accomplishment Instructions of Boeing Special Attention Service Bulletin 747-57-2326, dated
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
January 4, 2007.
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
Alternative Methods of Compliance (AMOCs)
(g)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.
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(2) To request a different method of compliance or a different compliance time for this AD, Lufttüchtigkeitsanweisung
follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which LTA-Nr.: D-2007-328
the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your local FSDO. Luftfahrt-Bundesamt
Datum der Bekanntgabe: 06.11.2007
Material Incorporated by Reference Muster: Hawker Beechcraft Corporation AD der ausländischen Behörde:
390 (Premier I / IA) FAA AD 2007-20-07 Amdt. 39-15217
(h) You must use Boeing Special Attention Service Bulletin 747-57-2327, Revision 1, dated July Geräte-Nr.: Technische Mitteilungen des Herstellers:
10, 2006; and Boeing Special Attention Service Bulletin 747-57-2326, dated January 4, 2007; as 2078, EASA.IM.A.073 Raytheon Mandatory Service Bulletin SB 24-3790 vom August
applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. 2006
The Director of the Federal Register approved the incorporation by reference of these documents in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Betroffenes Luftfahrtgerät:
Box 3707, Seattle, Washington 98124-2207, for a copy of this service information. You may review
copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or Hawker Beechcraft Corporation
390 (Premier I / IA)
at the National Archives and Records Administration (NARA). For information on the availability of
this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr- - Baureihen: Beechcraft (Raytheon) 390 Premier I und IA
locations.html.
Issued in Renton, Washington, on September 17, 2007. - Werk-Nrn.: RB-1 und RB-4 bis RB-149
John Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. 7 Betrifft:
[FR Doc. E7-18747 Filed 9-25-07; 8:45 am] STROMVERSORGUNG (ATA: 24): Starter-Generator - Inspektion / Auswechslung
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA 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 FAA Airworthiness Directive (AD) zu entnehmen. Die
Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten FAA
Airworthiness Directive (AD).
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2007-20-07 Amdt. 39-15217
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
***
5
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AIRWORTHINESS DIRECTIVE (2) If any starter-generator(s) specified As follows: Follow RAC
FAA in paragraph 3.A.(2) of RAC Mandatory (i) If both starter-generators are
Mandatory
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/ Service Bulletin SB 24-3790, Issued: Service
www.gpoaccess.gov/fr/advanced.html identified as being improperly
August, 2006, is/are found during the shimmed, replace at least one within 10
Bulletin SB 24-
inspection required in paragraph (e)(1) hours TIS after the inspection required
3790, Issued:
2007-20-07 Hawker Beechcraft Corporation (Type Certificate No. A00010WI previously held of this AD, replace that starter-generator in paragraph (e)(1) of this AD. Replace
August, 2006.
by Raytheon Aircraft Company): Amendment 39-15217; Docket No. FAA-2007-28068; with a properly shimmed starter- the other within the next 200 hours TIS
Directorate Identifier 2007-CE-043-AD. generator. after November 7, 2007 (the effective
date of this AD) or within the next 12
Effective Date months after November 7, 2007 (the
effective date of this AD), whichever
(a) This AD becomes effective on November 7, 2007. occurs first.
Affected ADs (ii) If one starter-generator is
identified as being improperly
(b) None. shimmed, replace it within the next 200
hours TIS after November 7, 2007 (the
Applicability effective date of this AD) or within the
next 12 months after November 7, 2007
(c) This AD applies to Model 390 airplanes, serial numbers RB-1 and RB-4 through RB-149, (the effective date of this AD),
that are certificated in any category. whichever occurs first.
(3) If a starter-generator specified in Not applicable. Follow RAC
Unsafe Condition paragraph 3.A.(2) of RAC Mandatory Mandatory
Service Bulletin SB 24-3790, Issued: Service
(d) This AD results from reports of a manufacturing error where certain starter-generators may August, 2006, is not found during the Bulletin SB 24-
have been improperly shimmed. We are issuing this AD to detect improperly shimmed starter- inspection required in paragraph (e)(1) 3790, Issued:
generators, which could result in premature starter-generator failure. This failure could lead to of this AD, no further action is required. August, 2006.
increased chances of dual starter-generator failure on the same flight.
(4) Do not install on any airplane any Before further flight after the inspection Follow RAC
Compliance RAC P/N 390-389001-0001 or AI P/N required in paragraph (e)(1) of this AD. Mandatory
MG94A-1 that is specified in paragraph Service
(e) To address this problem, you must do the following, unless already done: 3.A.(2) of RAC Mandatory Service Bulletin SB 24-
Bulletin SB 24-3790, Issued: August, 3790, Issued:
2006. August, 2006.
Actions Compliance Procedures
(1) Inspect the left-hand and right-hand Within the next 50 hours time-in- Follow RAC Alternative Methods of Compliance (AMOCs)
starter-generators, Raytheon Aircraft service (TIS) after November 7, 2007 Mandatory
Company (RAC) part number (P/N) 390- (the effective date of this AD) or within Service (f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve
389001-0001 or Advance Industries, Inc. the next 3 months after November 7, Bulletin SB 24- AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to
(AI) P/N MG94A-1, to determine the 2007 (the effective date of this AD), 3790, Issued: ATTN: Philip Petty, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room 100,
serial number and suffix letter as whichever occurs first. August, 2006. Wichita, Kansas 67209; telephone: (316) 946-4139; fax: (316) 946-4107; e-mail:
specified in paragraph 3.A.(2) of RAC philip.petty@faa.gov. Before using any approved AMOC on any airplane to which the AMOC
Mandatory Service Bulletin SB 24-3790, applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office
Issued: August, 2006. (FSDO), or lacking a PI, your local FSDO.
Material Incorporated by Reference
(g) You must use Raytheon Aircraft Company Mandatory Service Bulletin SB 24-3790, Issued:
August, 2006, to do the actions required by this AD, unless the AD specifies otherwise.
5 6
(1) The Director of the Federal Register approved the incorporation by reference of this service Lufttüchtigkeitsanweisung
information under 5 U.S.C. 552(a) and 1 CFR part 51. LTA-Nr.: D-2007-329
(2) For service information identified in this AD, contact Hawker Beechcraft Company, P.O.
Box 85, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140. Luftfahrt-Bundesamt
(3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Datum der Bekanntgabe: 07.11.2007
Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration Muster: Pacific Scientific AD der ausländischen Behörde:
(NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: Gutschloss-System EASA AD 2007-0256 vom 19.09.2007
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Geräte-Nr.: Technische Mitteilungen des Herstellers:
-keine- Pacific Scientific Service Bulletin No. SB 25-1111432 vom
Issued in Kansas City, Missouri, on September 24, 2007. 22.05.2007
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service. Betroffenes Luftfahrtgerät:
[FR Doc. E7-19192 Filed 10-2-07; 8:45 am]
Pacific Scientific
Gutschloss-System
- Baureihen: alle Pacific Scientific Gurtschlösser P/N 1111430-XX und 1111475-XX gemäß den
Angaben der EASA-AD, welche in der Zeit von November 2004 bis Mai 2007 hergestellt
wurden.
Diese Gurtschlösser sind eingebaut in, jedoch nicht ausschließlich beschränkt auf die
Luftfahrzeuge Eurocopter AS 350, AS 355, EC120, EC 130 und EC 155
- Werk-Nrn.: siehe Angaben unter ''Baureihen''
Betrifft:
Ausstattung/Ausrüstung (''Equipment and Furnishing - Seat Restraint System Plastic Rotary Buckle Handle -
Inspection/Replacement'')
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
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-2007-329 D-2007-329
placed on the restraint system, the straps may not release as intended when
EASA AIRWORTHINESS DIRECTIVE the buckle is rotated.
These circumstances are:
• a passenger who weights more than 50 kg and
AD No.: 2007 - 0256 • an aircraft upside down.
This could therefore result in a potential unsafe condition in event of an
emergency landing or when the occupant is bearing on the buckle.
The above is considered possible to take place for helicopters only and not for
Date: 19 September 2007 large aeroplanes.
This AD requires identification of all affected buckles, an inspection for cracks
and ultimate replacement of the entire batch of suspect buckles.
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. Effective Date: 03 October 2007
Type Approval Holder’s Name: Type/Model designations:
Compliance: Required as follows, unless already accomplished, in accordance with the
Pacific Scientific Company, Restraint Systems: 2000029, 2000067, instructions of Pacific Scientific SB 25-1111432 original issue dated May 22,
HTL/KIN-TECH Division 2000115 2007:
1. within 30 days after the effective date of this AD, inspect the seat
TSOA Number: various restraint systems, installed on seats or held as spare, to identify if
ETSOA Number: various, e.g. CAA UK Approval Number AR01193, AR0197, AR01199. the buckles part numbers are those affected by this AD; if yes,
check the buckles for integrity.
Foreign AD: None 2. Immediately replace any cracked buckle with an airworthy part or
mark the seat as “un-operative”.
Supersedure: None 3. In the 6 months following the effective date of this AD repeat
inspection of the buckles affected by this AD before any flight and
immediately replace them with an airworthy part if any start of
cracking is detected or mark the seat as “un-operative”. Not later
Equipment and Furnishing - Seat Restraint System Plastic Rotary than 6 months after the effective date of this AD, replace all rotary
ATA 25
Buckle Handle - Inspection/Replacement buckles, as identified in the Applicability section of this AD, with an
airworthy part.
Manufacturer: Pacific Scientific Company 4. After 6 months from the effective date of this AD, no person may
install on any aircraft as a replacement part any spare rotary buckle
having P/N 1111430-XX or 1111475-XX with a manufacturing date
Applicability: All the Pacific Scientific rotary buckles p/n’s 1111430-XX and 1111475-XX from November 2004 through May 2007 inclusive, or install any
used on restraint systems p/n’s: spare restraint system having the above mentioned buckle part
numbers and manufacturing date.
2000029-01 2000067-01 2000115-101
Ref. Publications: Pacific Scientific SB 25-1111432 issue dated May 22, 2007.
2000029-03 2000115-121
2000029-101
Remarks : 1. If requested and appropriately substantiated, EASA can accept Alternative
2000029-121 Methods of Compliance for this AD.
2. This AD was posted on 03 August 2007 as PAD 07-134 for consultation until
manufactured from November 2004 through May 2007 inclusive. 07 September 2007. The Comment Response Document can be found at
These p/n’s are known to be installed on, but not limited to, Eurocopter a/c http://ad.easa.europa.eu/ .
models AS 350, AS 355, EC120, EC 130, EC 155. 3. Enquiries regarding this AD should be referred to the AD Focal Point -
The applicability of this AD is limited to rotorcraft only and is not intended for Certification Directorate, EASA. E-mail: ADs@easa.europa.eu .
aeroplanes. 4. For any question concerning the technical content of the requirements in this
AD, please contact:
Reason: Pacific Scientific has received field reports of several instances of cracking on
the guarded rotary buckle assembly plastic handle part numbers 1111430-XX Pacific Scientific Aviation Services
and 1111475-XX with a date of manufacture from November 2004 through 11700 N.W. 102nd Rd. # 6
May 2007 inclusive. Miami, Florida 33178
United States
Preliminary testing performed by Pacific Scientific on buckle assemblies with Ph: 305-477-4711
cracked plastic handles indicates that in some circumstances when a load is Fax: 305-477-9799
1/3 2/3
D-2007-329
Lufttüchtigkeitsanweisung
Contact: Edel Mena LTA-Nr.: D-2007-330
www.pacscimiami.com
Luftfahrt-Bundesamt
Pacific Scientific UK Ltd.
Howarth Road, Maidenhead
Datum der Bekanntgabe: 07.11.2007
Berkshire SL6 1AP Muster: Embraer (Brasilien) AD der ausländischen Behörde:
United Kingdom ERJ-170 ANAC BAD 2007-08-03 Amdt. 39-1198 vom 27.08.2007
Ph: 44-1628 68-2200
Fax: 44-1628-68 2250 Geräte-Nr.: Technische Mitteilungen des Herstellers:
Contact: Ross Hamilton EASA.IM.A.001 Embraer Service Bulletin No. 170-34-0019
Pacific Scientific Germany
Unit 6 Hagen Park Betroffenes Luftfahrtgerät:
Miramstrasse 74
34123 Kassel Embraer (Brasilien)
Germany ERJ-170
Tel: + 49 (0) 561 57981 0
Fax: + 49 (0) 561 57981 25 - Baureihen: ERJ-170( )
Contact: Michael Hippe
- Werk-Nrn.: Alle
Betrifft:
Anzeige fehlerhafter Navigationsdaten auf beiden ''Primary Flight Displays'' ohne Warnung an die Flug-
besatzung durch technische Probleme mit den ''Inertial Reference Units (IRU)''.
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten ANAC
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-
führt 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 ANAC Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
ANAC Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
ANAC BAD 2007-08-03 Amdt. 39-1198 vom 27.08.2007
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
***
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CONTINUATION OF AD No.: 2007-08-03 - AMENDMENT 39-1198 PAGE No.: 2/2
For acquisition, contact:
National Civil Aviation Agency (ANAC)
Publications Branch
R. Santa Luzia, 651, 2º Mezanino, Centro
AGÊNCIA NACIONAL DE AVIAÇÃO CIVIL – BRAZIL Fax: 55 (21) 3814-6929
20030-040 – Rio de Janeiro - RJ, BRAZIL.
E-mail: publicacoes@anac.gov.br
BRAZILIAN AIRWORTHINESS DIRECTIVE
APPROVAL:
AD No.: 2007-08-03 Effective Date: 27 Aug. 2007 CLÁUDIO PASSOS SIMÃO
The following Brazilian Airworthiness Directive (AD), issued by the Agência Nacional de Aviação Civil General Manager
(ANAC) in accordance with provisions of Chapter IV, Title III of Código Brasileiro de Aeronáutica - Law No.
7,565 dated 19 December 1986 - and Regulamento Brasileiro de Homologação Aeronáutica (RBHA) 39, applies to GGCP
all aircraft registered in the Registro Aeronáutico Brasileiro. No person may operate an aircraft to which
this AD applies, unless it has previously complied with the requirements established herein.
MILTON ZUANAZZI
AD No. 2007-08-03 - EMBRAER - Amendment 39-1198. Director-President
ANAC
APPLICABILITY:
This Airworthiness Directive is applicable to all Embraer ERJ-170( ) aircraft models in
operation. NOTE: Original in Portuguese language signed and available in the files of the Aeronautical Products
Certification Branch (GGCP) of the National Civil Aviation Agency (ANAC).
CANCELLATION / REVISION:
Not applicable.
REASON:
It has been found that the implementation of the Inertial Reference Units (IRU) on the
ERJ-170 may lead, in certain degraded modes, to an erroneous Flight Path Angle (FPA) indication on
both Primary Flight Displays, with no alert to the flight crew. On the ERJ-170, FPA is considered as
important as pitch and bank angle for piloting purposes.
Since this condition affects flight safety, a corrective action is required. Thus, sufficient
reason exists to request compliance with this AD in the indicated time limit.
REQUIRED ACTION:
Removal of some wiring connections in the electrical connectors of both Inertial
Reference Units.
COMPLIANCE:
Required as indicated below, unless already accomplished.
Within the next 18 months after the effective date of this AD, remove the wiring
connections from pins 51 and 52 in the electrical connectors of both Inertial Reference Units.
The detailed instructions and procedures to accomplish this AD are described in the
Embraer Service Bulletin No. 170-34-0019 original issue, or further revisions approved by the ANAC.
Record compliance with this AD in the applicable maintenance log book.
CONTACT:
For additional technical information, contact:
National Civil Aviation Agency (ANAC)
Aeronautical Products Certification Branch (GGCP)
Av. Cassiano Ricardo, 521, Bloco B, 2º andar, Parque Residencial Aquarius
Fax: 55 (12) 3797-2330
12246-870 – São José dos Campos - SP, BRAZIL.
E-mail: pds@anac.gov.br
Form F-900-04E Form F-900-04E
D-2007-331
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2007-331
EASA Safety Information Notice
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 07.11.2007
Muster: Airbus AD der ausländischen Behörde:
No.: 2007 – 12
A330 EASA SIN 2007-12 vom 24.04.2007
A340 Issued: 24 April 2007
Geräte-Nr.: Technische Mitteilungen des Herstellers:
2849, 2850, EASA.A.004, EASA.A.015 Airbus Service Bulletin A330-25-3316
Airbus Service Bulletin A340-25-4277
Airbus Service Bulletin A340-25-5128
Subject: Equipment/Furnishing – Installation of a placard on
Betroffenes Luftfahrtgerät: passenger/crew and emergency exit doors
Airbus
A330, A340
Ref. Publication: AIRBUS Service Bulletin A330-25-3316
- Baureihen: alle A330-200, A330-300, A340-200 und A340-300 Baureihen AIRBUS Service Bulletin A340-25-4277
AIRBUS Service Bulletin A340-25-5128
- Werk-Nrn.: alle, gemäß den Angaben der EASA-Safety Information Notice (SIN) Or any later approved revision.
Betrifft: Introduction: During a scheduled slide or slide/raft deployment, some
Ausstattung/Ausrüstung (''Equipment/Furnishing – Installation of a placard on passenger/crew and emergency
operators experienced an unsuccessful slide deployment at
exit doors'')
passenger/crew and emergency exit doors.
Maßnahmen: Investigations revealed that the electrical harness has been
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA-SIN und der incorrectly routed during the previous slide
oben genannten Technischen Mitteilung des Herstellers zu entnehmen. removal/installation preventing the slide from falling and
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig
deploying normally during the test.
und innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen
This situation, if not corrected, could prevent the slide
Zustimmung durch das Luftfahrt-Bundesamt.
deployment and thus delay the emergency evacuation
At type design level, this situation has been covered by DGAC
Fristen: AD F-2005-077 mandating a one time inspection of the
Alle anzuwendenden Fristen sind der o. g. EASA-Safety Information Notice (SIN) zu entnehmen.
electrical harness routing.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der o. g. EASA-SIN.
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen AIRBUS have furthermore developed Service Bulletin (SB)
nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der A330-25-3316, SB A340-25-4277, SB A340-25-5128 to
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es heighten awareness during slide or slide/raft installation.
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Rechtsbehelfsbelehrung: This improvement developed by AIRBUS cannot be mandated
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder by EASA AD as the root cause “maintenance error” is not type
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. design related.
LTAs werden auch im Internet unter http://www.lba.de publiziert
*** The aim of this Service Information Notice (SIN) is to strongly
recommend installation of a placard at the lower door frame
lining for correct installation of the electrical harness to the
forward release rail.
Based upon their operational experience, NAAs may take
appropriate measures mandating the suggested corrective
action to this unsafe condition.
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