Nachrichten für Luftfahrer 2007 Teil II (weicht ggf. von Druckversion ab)
Inspection Report and Disposition of Damaged Parts
(k) For Model 737-100, -200, -300, -400, and -500 series airplanes: At the applicable time
specified in paragraph (k)(1) or (k)(2) of this AD, submit a report of the findings (both positive and
negative) of any inspection required by paragraph (i) or (j) of this AD and send any damaged parts to
the manufacturer, as described in Boeing Service Bulletin 737-28A1263, Revision 2, dated August
10, 2007. The report must include the inspection results, a description of any discrepancies found, the
airplane serial number, and the number of landings and flight hours on the airplane. Under the
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and
Budget (OMB) has approved the information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
(1) For any inspection done after the effective date of this AD: Submit the report within 30 days
after the inspection.
(2) For any inspection done before the effective date of this AD: Submit the report within 30
days after the effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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.
(2) To request a different method of compliance or a different compliance time for this AD,
follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which
the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your local FSDO.
(3) AMOCs approved previously in accordance with AD 99-21-15, amendment 39-11360, and
AD 2007-11-07 are approved as AMOCs for the corresponding provisions of this AD.
Material Incorporated by Reference
(m) You must use applicable Boeing service bulletins specified in Table 1 of this AD to perform
the actions that are required by this AD, unless the AD specifies otherwise.
Table 1.–All Material Incorporated by Reference
Service Bulletin Revision Date
Level
Boeing Alert Service Bulletin 737-28A1263 1 March 19, 2007
Boeing Service Bulletin 737-28A1263 2 August 10, 2007
(1) The Director of the Federal Register approved the incorporation by reference of Boeing
Service Bulletin 737-28A1263, Revision 2, dated August 10, 2007, in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On June 6, 2007 (72 FR 28597, May 22, 2007), the Director of the Federal Register approved
the incorporation by reference of Boeing Alert Service Bulletin 737-28A1263, Revision 1, dated
March 19, 2007.
(3) Contact Boeing Commercial Airplanes, P.O. 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 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.
Issued in Renton, Washington, on November 8, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-22724 Filed 11-20-07; 8:45 am]
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2006-141R1
ersetzt: D-2006-141
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 27.11.2007
Muster: Boeing AD der ausländischen Behörde:
BOEING 747 FAA AD 2007-23-18 Amdt. 39-15266
Geräte-Nr.: Technische Mitteilungen des Herstellers:
2832 Boeing Alert Service Bulletin 747-53A2507 vom 21.04.2005
Betroffenes Luftfahrtgerät:
Boeing
BOEING 747
- Baureihen: 747-100B SUD, 747-300, 747-400, 747-400D und 747-200B mit verlängertem Oberdeck
- Werk-Nrn.: Alle
Betrifft:
RUMPF (ATA: 53): Langes Oberdeck - Rumpfspante und Querprofile (STA1120 bis STA1220) - Inspektion
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).
HINWEIS: Die in der AD 2007-23-18 aufgeführte AD 2004-07-22 ist per LTA D-1985-020R5 angeordnet.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2007-23-18 Amdt. 39-15266
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-2006-141 vom 11.05.2006) Aktenzeichen: (01)T232-502.1/D-2006-141R1 Seite 1 von 1
AIRWORTHINESS DIRECTIVE
FAA
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html
2007-23-18 Boeing: Docket No. FAA-2007-0194; Directorate Identifier 2007-NM-306-AD;
Amendment 39-15266.
Effective Date
(a) This AD becomes effective November 28, 2007.
Affected ADs
(b) This AD affects the following ADs:
(1) This AD supersedes AD 2006-06-11.
(2) As of the effective date of this AD, for the areas inspected in accordance with this AD,
accomplishment of the requirements of paragraph (f) or (i) of this AD terminates the corresponding
inspection requirements for the upper deck tension ties as required by paragraphs (c) and (d) of AD
2004-07-22, amendment 39-13566, as those paragraphs apply to inspections of structural significant
item (SSI) F-19A, as identified in Boeing Document No. D6-35022, ‘‘Supplemental Structural
Inspection Document,'' Revision G, dated December 2000. All other requirements of AD 2004-07-22
continue to apply.
Applicability
(c) This AD applies to all Boeing Model 747-100B SUD, 747-300, 747-400, and 747-400D
series airplanes; and Model 747-200B series airplanes having a stretched upper deck; certificated in
any category.
Unsafe Condition
(d) This AD results from new reports of multiple severed adjacent tension ties, in addition to the
previous reports of cracked and severed tension ties, broken fasteners, and cracks in the frame, shear
web, and shear ties adjacent to tension ties for the upper deck. We are issuing this AD to detect and
correct cracking of the tension ties, shear webs, and frames of the upper deck, which could result in
rapid decompression and reduced structural integrity of the airplane.
Compliance
(e) You are responsible for having the actions required by this AD performed within the
compliance times specified, unless the actions have already been done.
Repetitive Stage 1 Inspections
(f) Do detailed inspections for cracking or discrepancies of the fasteners in the tension ties, shear
webs, and frames at body stations 1120 through 1220, and related investigative and corrective actions
as applicable, by doing all actions specified in and in accordance with ‘‘Stage 1 Inspection'' of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2507, dated April 21, 2005,
except as provided by paragraph (j) of this AD. Do the Stage 1 inspections at the applicable times
specified in paragraphs (g) and (h) of this AD, except as provided by paragraphs (f)(1) and (f)(2) of
this AD. Any applicable related investigative and corrective actions must be done before further
flight.
(1) Where paragraph 1.E., ‘‘Compliance,'' of the service bulletin specifies a compliance time
relative to the original issue date of the service bulletin, this AD requires compliance before the
specified compliance time after April 26, 2006 (the effective date of AD 2006-06-11).
(2) For any airplane that reaches the applicable compliance time for the initial Stage 2 inspection
(as specified in Table 1, Compliance Recommendations, under paragraph 1.E. of the service bulletin)
before reaching the applicable compliance time for the initial Stage 1 inspection: Accomplishment of
the initial Stage 2 inspection eliminates the need to do the Stage 1 inspections.
Compliance Time for Initial Stage 1 Inspection
(g) Do the initial Stage 1 inspection at the earlier of the times specified in paragraphs (g)(1) and
(g)(2) of this AD.
(1) At the earlier of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) At the applicable time specified in paragraph 1.E., ‘‘Compliance,'' of Boeing Alert Service
Bulletin 747-53A2507, dated April 21, 2005.
(ii) Before the accumulation of 10,000 total flight cycles, or within 250 flight cycles after the
effective date of this AD, whichever occurs later.
(2) At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Before the accumulation of 12,000 total flight cycles.
(ii) Within 50 flight cycles or 20 days, whichever occurs first, after the effective date of this AD.
Compliance Times for Repetitive Stage 1 Inspections
(h) Repeat the Stage 1 inspection specified in paragraph (f) of this AD at the time specified in
paragraph (h)(1) or (h)(2), as applicable. Repeat the inspection thereafter at intervals not to exceed
250 flight cycles, until the initial Stage 2 inspection required by paragraph (i) of this AD has been
done.
(1) For airplanes on which the initial Stage 1 inspection had not been accomplished as of the
effective date of this AD: Do the next inspection before the accumulation of 10,000 total flight
cycles, or within 250 flight cycles after the initial Stage 1 inspection done in accordance with
paragraph (f) of this AD, whichever occurs later.
(2) For airplanes on which the initial Stage 1 inspection had been accomplished as of the
effective date of this AD: Do the next inspection at the applicable time specified in paragraph
(h)(2)(i) or (h)(2)(ii) of this AD.
(i) For airplanes that had accumulated fewer than 12,000 total flight cycles as of the effective
date of this AD: Do the next inspection before the accumulation of 10,000 total flight cycles, or
within 250 flight cycles after the effective date of this AD, whichever occurs later.
(ii) For airplanes that had accumulated 12,000 total flight cycles or more as of the effective date
of this AD: Do the next inspection at the later of the times specified in paragraphs (h)(2)(ii)(A) and
(h)(2)(ii)(B) of this AD.
(A) Within 250 flight cycles after accomplishment of the initial Stage 1 inspection.
(B) Within 50 flight cycles or 20 days, whichever occurs first, after the effective date of this AD.
Repetitive Stage 2 Inspections
(i) Do detailed and high frequency eddy current inspections for cracking or discrepancies of the
fasteners in the tension ties, shear webs, and frames at body stations 1120 through 1220, and related
investigative and corrective actions as applicable, by doing all actions specified in and in accordance
with ‘‘Stage 2 Inspection'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2507, dated April 21, 2005, except as provided by paragraph (j) of this AD. Do the initial and
repetitive Stage 2 inspections at the applicable times specified in paragraph 1.E., ‘‘Compliance,'' of
the service bulletin. Any applicable related investigative and corrective actions must be done before
further flight. Accomplishment of the initial Stage 2 inspection ends the repetitive Stage 1
inspections.
Exception to Corrective Action Instructions
(j) If any discrepancy; including but not limited to cracking, or broken, loose, or missing
fasteners; is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747-
53A2507, dated April 21, 2005, specifies to contact Boeing for appropriate action: Before further
flight, repair the discrepancy using a method approved in accordance with the procedures specified in
paragraph (l) of this AD.
Reporting Requirement
(k) At the applicable time specified in paragraph (k)(1) or (k)(2) of this AD, submit a report of
the findings (both positive and negative) of each Stage 1 inspection required by this AD to Boeing
Commercial Airplanes; Attention: Manager, Airline Support; P.O. Box 3707 MC 04-ER; Seattle,
Washington 98124-2207; fax (425) 266-5562. The report must include the inspection results, a
description of any discrepancies found, the inspections performed, the airplane serial number, and the
number of total accumulated flight cycles on the airplane. Under the provisions of the Paperwork
Reduction Act (44 U.S.C. 3501, et seq.), the Office of Management and Budget (OMB) has approved
the information collection requirements contained in this AD and has assigned OMB Control Number
2120-0056.
(1) For any inspection done after the effective date of this AD: Submit the report within 30 days
after the inspection.
(2) For any inspection done before the effective date of this AD: Submit the report within 30
days after the effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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.
(2) To request a different method of compliance or a different compliance time for this AD,
follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which
the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your local FSDO.
(3) An AMOC that provides an acceptable level of safety may be used for any repair required by
this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized by the Manager, Seattle
ACO, to make those findings. For a repair method to be approved, the repair must meet the
certification basis of the airplane, and the approval must specifically refer to this AD.
(4) AMOCs approved previously for repairs for compliance with AD 2006-06-11 are approved
as AMOCs for the corresponding provisions of this AD provided that the repaired areas are inspected
at the times specified in this AD, and the inspections are done in accordance with this AD.
Material Incorporated by Reference
(m) You must use Boeing Alert Service Bulletin 747-53A2507, dated April 21, 2005, to perform
the actions that are required by this AD, unless the AD specifies otherwise. The Director of the
Federal Register approved the incorporation by reference of this document on April 26, 2006 (71 FR
14367, March 22, 2006). Contact Boeing Commercial Airplanes, P.O. 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 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
.
Issued in Renton, Washington, on November 15, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 07-5794 Filed 11-21-07; 8:45 am]
BILLING CODE 4910-13-P
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2006-214R2
ersetzt: D-2006-214R1
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 16.11.2007
Muster: TURBOMECA AD der ausländischen Behörde:
TURMO IV EASA AD 2007-0254 vom 14.09.2007
Geräte-Nr.: Technische Mitteilungen des Herstellers:
DGAC TCDS M-8 TURBOMECA Maintenance Manual 279 02 931
TURBOMECA Mandatory Service Bulletin A249 72 0231
TURBOMECA Mandatory Service Bulletin A249 72 0802 Rev. 2
Betroffenes Luftfahrtgerät:
TURBOMECA
TURMO IV
- Baureihen: TURMO IV Serie
- Werk-Nrn.: Alle Triebwerke dieser Baureihen, die mit Ölleitungen mit den folgenden Hersteller-Teile-
nummern (P/N's) ausgerüstet sind:
0 249 92 808 0
0 249 92 813 0
0 249 92 916 0
Betrifft:
Möglicher Triebwerksausfall im Fluge durch Undichtigkeiten an der flexiblen Ölleitung zwischen Öltank und
Ölkühler und zwischen ''Intermediate Bearing'' und Ölpumpe aufgrund eines Produktionsfehlers bei der
Herstellung der Ölleitungen.
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
Airworthiness Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen.
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
vollständig und innerhalb der 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 EASA Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
EASA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA AD 2007-0254 vom 14.09.2007
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
***
(LTA-Nr.: D-2006-214R1 vom 08.03.2007) Aktenzeichen: (10)T23-502.1/D-2006-214R2 Seite 1 von 1
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2007- 0254
Date: 14 September 2007
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.
Type Approval Holder’s Name : Type/Model designation(s) :
TURBOMECA TURMO turboshaft engines
TCDS Number : DGAC France M8
Foreign AD : not applicable
Supersedure : EASA AD 2007-0061-E released on 07 March 2007
Engine - Flexible lubrication pipes between tank and cooler and
ATA 72 between intermediate bearing and oil pump -
Inspection/Replacement
Manufacturer(s): TURBOMECA
all TURMO IV turboshaft engines fitted with an oil pipe P/N 0 249 92 813 0
or 0 249 92 916 0 or 0 249 92 808 0.
Applicability:
These engines are known to be installed in, but are not limited to,
Eurocopter SA 330 F, G or J PUMA helicopters.
Several occurrences of deterioration of:
- the oil pipe P/N 0 249 92 813 0 installed on TURMO III C4 between the
oil cooler and the tank; and of
- the oil pipe P/N 0 249 92 808 0 installed on TURMO III C4 and
TURMO IV C between the intermediate bearing and the oil pump;
Reason: have been reported to Turbomeca. Most, but not all, reported occurrences
concerned military models. Such deterioration and oil leakage can lead to
commanded engine in flight shut down.
The cause of the pipe deterioration is linked to a manufacturing process
change applied by the manufacturer of the pipes in 2003.
This Airworthiness Directive (AD) applies to oil pipes P/N 0 249 92 813 0,
0 249 92 916 0 and 0 249 92 808 0, which are the same as, or similar to, the
deteriorated pipes in military models.
AD 2007-0254 1/3
The present AD retains requirements of the superseded AD 2007-0061-E
and in addition mandates Turbomeca Service Bulletin 249 72 0231 or
modification TU 231 (replacement of flexible lubrication pipe between cooler
and tank) for engines equipped with a pipe P/N 0 249 92 813 0 or
0 249 92 916 0 vulcanised in the 2nd quarter of 2003 or later.
TU 231 introduces a new pipe, P/N 9 560 17 601 0, which allows the
maintenance to be limited to the activities defined in the Maintenance
Manual.
Effective Date: 28 September 2007
PREVIOUS REQUIREMENTS OF AD 2007-0061-E
1- For engines equipped with oil pipe P/N 0 249 92 813 0 or 0 249 92 916 0
or 0 249 92 808 0, unless already performed, the following actions are
mandatory, from 09 March 2007 ( the effective date of AD 2007-0061-E).
Before next flight:
- Identify the vulcanisation batch of the oil pipe.
- If the pipe was vulcanised in the 2nd quarter of 2003 or later
(ex.: marking 2T03 refers to the 2nd quarter of 2003):
- Inspect the oil filter for black particles which could come from
internal deterioration of the pipe.
- Inspect the engine bay for possible oil leakage from the pipe.
- Perform a boroscope inspection of the pipe.
2- If both engines installed on a given helicopter are equipped with pipes
P/N 0 249 92 813 0 or 0 249 92 916 0 which where vulcanised after the
first quarter of 2003, replace one of the two pipes before the next flight.
Compliance:
3- After 25 additional Flight Hours (FH), repeat the inspections required by
paragraph 1 of this AD.
NEW REQUIREMENT OF THIS AD:
4- For engines equipped with oil pipe P/N 0 249 92 813 0 or 0 249 92 916 0
vulcanised in the 2nd quarter of 2003 or later, within the next 50 FH after
the effective date of this AD or before the 31 December 2007 whichever
occurs first, replace the pipe with P/N 9 560 17 601 0 per modification
TU 231.
NOTE 1: Inspection for oil leak before and after flight, and inspection of the
oil filter every 25 hours, as defined in the Engine Maintenance
Manual, remain applicable.
NOTE 2: The detailed procedures to comply with the requirements of this AD
are defined in the referenced TURBOMECA Mandatory Service
Bulletins A249 72 0802 and 249 72 0231.
TURBOMECA Mandatory Service Bulletin A249 72 0802 Update No. 2
TURBOMECA Mandatory Service Bulletin 249 72 0231 Original issue
Ref. Publications: (any later EASA approved revision of these documents is acceptable).
TURBOMECA Maintenance Manual 279 02 931.
Remarks : 1. If requested and appropriately substantiated, EASA can accept
Alternative Methods of Compliance for this AD.
AD 2007-0254 2/3
