Nachrichten für Luftfahrer 2009 Teil II (weicht ggf. von Druckversion ab)
[Federal Register: June 25, 2009 (Volume 74, Number 121)]
[Rules and Regulations]
Lufttüchtigkeitsanweisung [Page 30211]
LTA-Nr.: D-2009-103R1 From the Federal Register Online via GPO Access [wais.access.gpo.gov]
ersetzt: D-2009-103 [DOCID:fr25jn09-1]
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 07.08.2009
––––––––––––––––––––––––––––––––––
Muster: Pratt & Whitney AD der ausländischen Behörde:
JT9D FAA AD 2009-04-18 Correction Amdt. 39-15824
DEPARTMENT OF TRANSPORTATION
Geräte-Nr.: Technische Mitteilungen des Herstellers:
6311 Pratt & Whitney Alert Service Bulletin JT9D A6488 Revision 1 vom Federal Aviation Administration
18.04.2008
Pratt & Whitney JT9D Engine Maintenance Manual P/N 770408
Section 72-51-00, Assembly-02 Revision 122, Seite 1001 bis 1036 14 CFR Part 39
vom 15.02.2008
[Docket No. FAA-2008-0759; Directorate Identifier 2008-NE-02-AD; Amendment 39-15824;
Betroffenes Luftfahrtgerät: AD 2009-04-18]
Pratt & Whitney RIN 2120-AA64
JT9D
- Baureihen: JT9D-7, -7A, -7AH, - 7H, -7F und -7J Airworthiness Directives; Pratt & Whitney (PW) JT9D-7 Series Turbofan Engines; Correction
- Werk-Nrn.: Alle AGENCY: Federal Aviation Administration, DOT.
Betrifft: ACTION: Final rule; correction.
Möglicher Triebwerksausfall im Fluge durch Bruch der Stufe 2 Hochdruckturbinenscheibe.
––––––––––––––––––––––––––––––––––
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA
Airworthiness Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen. SUMMARY: The FAA is correcting airworthiness directive (AD) 2009-04-18, which was
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, previously published in the Federal Register. That AD applies to PW models JT9D-7, -7A, -7AH, -
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente 7H, -7F, and -7J turbofan engines. The two references to the engine manual in paragraph (h) and in
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits- Table 1, are incomplete. This document corrects those references. In all other respects, the original
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
document remains the same.
Fristen:
Alle anzuwendenden Fristen sind der oben genannten FAA Airworthiness Directive zu entnehmen. DATES: Effective Date: Effective June 25, 2009.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
FAA Airworthiness Directive. FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park,
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2009-04-18 Correction Amdt. 39-15824
Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238-7117; fax (781) 238-
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen 7199, for more information about this AD.
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. SUPPLEMENTARY INFORMATION: On March 31, 2009 (74 FR 14458), we published a final
Rechtsbehelfsbelehrung:
rule AD, FR Doc, E9-6749, in the Federal Register. That AD applies to PW models JT9D-7, -7A, -
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder 7AH, -7H, -7F, and -7J turbofan engines. We need to make the following corrections:
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
LTAs werden auch im Internet unter http://www.lba.de publiziert § 39.13 [Corrected]
***
On page 14459, in Table 1, in the first column, in the second line, ''770408'' is corrected to read
''770408, Section 72-51-00, Assembly-02''.
On page 14459, in the third column, in paragraph (h), in the third line, ''1.B.(32) of the JT9D-7
Engine Manual'' is corrected to read ''1.B.(32) of Section 72-51-00, Assembly-02 of the JT9D-7
Engine Manual''.
1
(LTA-Nr.: D-2009-103 vom 24.04.2009) Aktenzeichen: (10)T23-502.1/D-2009-103R1 Seite 1 von 1
Issued in Burlington, Massachusetts, on June 17, 2009. [Federal Register: March 31, 2009 (Volume 74, Number 60)]
Carlos Pestana, [Rules and Regulations]
Acting Manager, Engine and Propeller Directorate, [Page 14458-14460]
Aircraft Certification Service. From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31mr09-2]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0759; Directorate Identifier 2008-NE-02-AD; Amendment 39-15824;
AD 2009-04-18]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney (PW) JT9D-7 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for PW models JT9D-7, -7A,
-7AH, -7H, -7F, and -7J turbofan engines. This AD requires initial and repetitive borescope
inspections of the 2nd stage high-pressure turbine (HPT) rotor and stator assembly. This AD results
from an uncontained failure of a 2nd stage HPT rotor disk that caused the engine to separate from the
airplane. We are issuing this AD to prevent failure of the 2nd stage HPT rotor disk, which could
result in uncontained engine failure, damage to the airplane, and the engine separating from the
airplane.
DATES: This AD becomes effective May 5, 2009. The Director of the Federal Register approved the
incorporation by reference of certain publications listed in the regulations as of May 5, 2009.
ADDRESSES: You can get the service information identified in this AD from Pratt & Whitney, 400
Main St., East Hartford, CT 06108; telephone (860) 565-8770; fax (860) 565-4503.
The Docket Operations office is located at Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12-140,
Washington, DC 20590-0001.
FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park,
Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-
7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a
proposed AD. The proposed AD applies to PW models JT9D-7, -7A, -7AH, -7H, -7F, and -7J
turbofan engines. We published the proposed AD in the Federal Register on July 10, 2008 (73 FR
2 3
39627). That action proposed to require an initial and repetitive borescope inspection of the 2nd stage national government and the States, or on the distribution of power and responsibilities among the
HPT vane assembly. various levels of government.
For the reasons discussed above, I certify that this AD:
Examining the AD Docket (1) Is not a ''significant regulatory action'' under Executive Order 12866;
(2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034,
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at February 26, 1979); and
the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal (3) Will not have a significant economic impact, positive or negative, on a substantial number of
holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and small entities under the criteria of the Regulatory Flexibility Act.
other information. The street address for the Docket Operations office (telephone (800) 647-5527) is We prepared a summary of the costs to comply with this AD and placed it in the AD Docket.
provided in the ADDRESSES section. Comments will be available in the AD docket shortly after You may get a copy of this summary at the address listed under ADDRESSES.
receipt.
We provided the public the opportunity to participate in the development of this AD. We have List of Subjects in 14 CFR Part 39
considered the comment received.
One commenter asks us to change the compliance time from ''cycles-since-overhaul'' to ''cycles- Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
since-last installation of the second stage HPT vanes.'' The commenter states that second stage HPT
vanes might be removed and replaced at times other than module overhaul, such as for module repair. Adoption of the Amendment
We agree. We changed paragraph (f) of the proposed AD from ''Within 100 cycles-in-service
(CIS) after the effective date of this AD, or within 1,000 CIS after the last HPT module overhaul * * Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation
*'' to ''Within 100 cycles-in-service (CIS) after the effective date of this AD, or within 1,000 CIS after Administration amends 14 CFR part 39 as follows:
the last installation of the second stage HPT vanes * * *''
PART 39–AIRWORTHINESS DIRECTIVES
Conclusion
1. The authority citation for part 39 continues to read as follows:
We have carefully reviewed the available data, including the comment received, and determined
that air safety and the public interest require adopting the AD with the changes described previously. Authority: 49 U.S.C. 106(g), 40113, 44701.
We have determined that these changes will neither increase the economic burden on any operator
nor increase the scope of the AD. § 39.13 [Amended]
Costs of Compliance 2. The FAA amends § 39.13 by adding the following new airworthiness directive:
We estimate that this AD will affect 240 engines installed on airplanes of U.S. registry. We also
estimate that it will take about 5 work-hours per engine to perform the proposed actions, that each
engine might require two inspections, and that the average labor rate is $80 per work-hour. Based on
these figures, we estimate the total cost of the AD to U.S. operators to be $192,000.
Authority for This Rulemaking
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
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,
Section 44701, ''General requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in air commerce. This
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.
Regulatory Findings
We have determined that this AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States, on the relationship between the
4 5
AIRWORTHINESS DIRECTIVE (1) Use the Accomplishment Instructions of PW ASB JT9D A6488 Revision 1, dated April 18,
FAA 2008, to borescope-inspect the 2nd stage HPT rotor and stator assembly either on-wing or in the
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/ shop.
www.gpoaccess.gov/fr/advanced.html (2) If you see any damage or contact between the 2nd stage HPT vanes and the 2nd stage HPT
rotor, remove the engine from service.
CORRECTION: [Federal Register: June 25, 2009 (Volume 74, Number 121)]; Page 30211;
www.access.gpo.gov/su_docs/aces/aces140.html] Optional Terminating Action
2009-04-18 Pratt & Whitney: Amendment 39-15824. Docket No. FAA-2008-0759; Directorate (h) Installing the 2nd stage HPT vanes as specified in paragraphs 1.B.(1) through 1.B.(32) of
Identifier 2008-NE-02-AD. Section 72-51-00, Assembly-02 of the JT9D-7 Engine Manual Revision 122, dated February 15,
2008, terminates the repetitive inspection requirement specified in paragraph (g) of this AD.
Effective Date
Alternative Methods of Compliance
(a) This airworthiness directive (AD) becomes effective May 5, 2009.
(i) The Manager, Engine Certification Office, has the authority to approve alternative methods of
Affected ADs compliance for this AD if requested using the procedures found in 14 CFR 39.19.
(b) None. Related Information
Applicability (j) Contact Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine and
Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail:
(c) This AD applies to Pratt & Whitney (PW) JT9D-7, -7A, -7AH, -7H, -7F, and -7J turbofan kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199, for more information about
engines. These engines are installed on, but not limited to, Boeing 747 series airplanes. this AD.
Unsafe Condition Material Incorporated by Reference
(d) This AD results from an uncontained failure of a 2nd stage high-pressure turbine (HPT) rotor (k) You must use the service information specified in the following Table 1 to perform the
disk that caused the engine to separate from the airplane. We are issuing this AD to prevent failure of actions required by this AD. The Director of the Federal Register approved the incorporation by
the 2nd stage HPT rotor disk, which could result in uncontained engine failure, damage to the reference of the documents listed in the following Table 1 in accordance with 5 U.S.C. 552(a) and 1
airplane, and the engine separating from the airplane. CFR part 51. Contact Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone
(860) 565-8770; fax (860) 565-4503, for a copy of this service information. You may review copies
Compliance 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
(e) You are responsible for having the actions required by this AD performed within the material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-
compliance times specified unless the actions have already been done. locations.html.
Initial Borescope Inspection Table 1–Incorporation by Reference
Service information No. Page Revision Date
(f) Within 100 cycles-in-service (CIS) after the effective date of this AD, or within 1,000 CIS
after the last installation of the second stage HPT vanes, whichever occurs later, do the following: Pratt & Whitney JT9D Engine 1001 through 1036 122 February 15, 2008.
(1) Use the Accomplishment Instructions of PW Alert Service Bulletin (ASB) JT9D A6488, Maintenance Manual PN 770408, Section
Revision 1, dated April 18, 2008, to borescope-inspect the 2nd stage HPT rotor and stator assembly 72-51-00, Assembly-02
either on-wing or in the shop. Total Pages—36
(2) If you see any damage or contact between the 2nd stage HPT vanes and the 2nd stage HPT
rotor, remove the engine from service. Pratt & Whitney PW ASB JT9D A6488, All 1 April 18, 2008.
Revision 1, dated April 18, 2008.
Repetitive Borescope Inspection Total Pages—21
(g) Thereafter, within 1,000 cycles-since-last inspection, do the following:
6 7
Issued in Burlington, Massachusetts, on March 17, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Lufttüchtigkeitsanweisung
Aircraft Certification Service. LTA-Nr.: D-2009-149R1
ersetzt: D-2009-149
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 14.08.2009
Muster: BOMBARDIER Inc. AD der ausländischen Behörde:
DHC-8-400 TC AD CF-2009-25R1 vom 23.07.2009
Geräte-Nr.: Technische Mitteilungen des Herstellers:
2868, EASA.IM.A.191 Bombardier Service Bulletin 84-27-37 vom 05.02.2009
Bombardier Service Bulletin 84-27-39 vom 05.02.2009
Betroffenes Luftfahrtgerät:
BOMBARDIER Inc.
DHC-8-400
- Baureihen: DHC-8-400, DHC-8-401 und DHC-8-402
- Werk-Nrn.: 4105 bis 4179
Betrifft:
(ATA 27) Spoiler Unload Valves and Rudder Shutoff Valves - Non-Conformance / Incorrect Wall Thickness -
Inspection / Replacement
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten Transport Canada
(TC) Airworthiness Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen. Alle
erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und
innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen
Zustimmung durch das Luftfahrt-Bundesamt.
Fristen:
Alle anzuwendenden Fristen sind der oben genannten TC Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
TC Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
TC AD CF-2009-25R1 vom 23.07.2009
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
8
(LTA-Nr.: D-2009-149 vom 04.06.2009) Aktenzeichen: (01)T231-502.1/D-2009-149R1 Seite 1 von 1
Transport Transports TP 7245E No.
Nq
CF-2009-25R1 2/2
Canada Canada No.
1/2
CF-2009-25R1
Issue Date Inspect the left hand and right hand rudder shutoff valves P/N 412700-1001 for
23 July 2009 leaking or weeping in accordance with Bombardier SB 84-27-39, dated
February 5, 2009, or later revisions approved by the Chief, Continuing Airworthiness,
AIRWORTHINESS DIRECTIVE Transport Canada
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 2.1. If leaking or weeping is found, prior to further flight, replace the affected rudder
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. shutoff valve with a new valve.
This AD has been issued by the Continuing Airworthiness Division (AARDG),National Aircraft Certification Branch, Transport Canada, Ottawa, telephone 613 952-4357.
2.2. If no leaking or weeping is found, replace the inspected valve(s) within 6 000
Number: CF-2009-25R1
hours air time from the time of initial inspection mandated by this directive.
Subject: Spoiler Unload Valves and Rudder Shutoff Valves – Non-Conformance - Incorrect 3. As of the effective date of this directive, no replacement of Spoiler Unload Valves
Wall Thickness Assembly P/N 396000-1005, with serial numbers from 0289 through 0424 and
Rudder Shutoff Valves P/N 412700-1001 with serial numbers from 0239 through
Effective: 12 August 2009 0384, are allowed to be installed on the DHC-8 Series 400 airplanes unless such
valves have been inspected by the manufacturer and labeled with a suffix “A” after
Applicability: Bombardier Inc. Models DHC-8-400, DHC-8-401 and DHC-8-402, Serial Numbers 4105 the Serial Number as indicated in the above-mentioned Service Bulletins.
thru 4179.
Authorization: For Minister of Transport, Infrastructure and Communities
Compliance: As indicated unless already accomplished
Background: During final Acceptance Test Procedure (ATP), a small oil leak was discovered on the
Spoiler Unload Valve and Rudder Shutoff Valve bodies. Investigation revealed that a Anthony Wan
number of valves were manufactured with an incorrect wall thickness. This thin wall Acting Chief, Continuing Airworthiness
condition caused cracking, subsequent external weeping and pressure loss from the
subject valves. Contact: Mr. Gordanko Jeremic, Continuing Airworthiness, Ottawa, telephone 613-952-4379,
facsimile 613-996-9178 or e-mail gordanko.jeremic@tc.gc.ca or any Transport Canada
This condition, if not corrected, will cause a loss of hydraulic fluid and subsequent loss of Centre.
spoiler and/or rudder control.
Revision 1 of this directive mandates a new interval for the initial inspection, clarifies the
time for replacement of the valve(s) specified in Paragraphs 1.2 and 2.2, and clarifies the
labeling of the inspected valves in Paragraph 3 of this directive.
Corrective Within 750 hours air time after the effective date of this directive, accomplish the
Actions: following:
1. Spoiler Unload Valve Manifold – Applicable to DHC-8 Aircraft, Models 400, 401, and
402, Serial Numbers 4105 through 4172:
Inspect the left hand and right hand spoiler unload valves Part Number (P/N)
396000-1005 for leaking or weeping in accordance with Bombardier Service Bulletin
(SB) 84-27-37, dated February 5, 2009, or later revisions approved by the Chief,
Continuing Airworthiness, Transport Canada.
1.1. If leaking or weeping is found, prior to further flight, replace the affected spoiler
unload valve with a new valve.
1.2. If no leaking or weeping is found, replace the inspected valve(s) within 6 000
hours air time from the time of initial inspection mandated by this directive.
2. Rudder Shutoff Valve Manifold – Applicable to DHC-8 Aircraft, Models 400, 401, and
402, Serial Numbers 4113 through 4179:
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)
EASA AD No : 2009-0181-E
Lufttüchtigkeitsanweisung EASA EMERGENCY AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2009-158R1
ersetzt: D-2009-158 AD No.: 2009-0181-E
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 14.08.2009
Muster: BAE Systems (Operations) Ltd. AD der ausländischen Behörde:
HP 137 Mark 1 / JETSTREAM 200 EASA Emergency AD 2009-0181-E vom 12.08.2009 Date: 12 August 2009
JETSTREAM SERIES 3100 / 3200
Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance
Geräte-Nr.: Technische Mitteilungen des Herstellers: with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States
2526, EASA.A.191, CAAUK BA4 BAE Systems Alert Service Bulletin 32-A-JA090640 Revision 2 and of the European third countries that participate in the activities of EASA under Article 66 of
that Regulation.
vom 11.08.2009
APPH Service Bulletin 1847-32-14 vom Juni 2009 This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the
APPH Service Bulletin 1862-32-14 vom Juni 2009 continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an
aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EC
2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
Betroffenes Luftfahrtgerät:
Type Approval Holder’s Name : Type/Model designation(s) :
BAE Systems (Operations) Ltd.
HP 137 Mark 1 / JETSTREAM 200, JETSTREAM SERIES 3100 / 3200 BAE Systems (Operations) Ltd HP 137 Jetstream MK 1, Jetstream Series
200, 3100 and 3200 aeroplanes
- Baureihen: Alle
TCDS Numbers : UK BA4 and EASA.A.191
- Werk-Nrn.: Alle
Foreign AD : Not applicable
Betrifft:
(ATA 32) Landing Gear - Main Landing Gear Radius Rod - Identification / Replacement Supersedure : This AD supersedes EASA Emergency AD 2009-0121-E dated 09 June 2009.
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen. Landing Gear – Main Landing Gear Radius Rod – Identification /
ATA 32
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, Replacement
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt. Handley Page Ltd, Scottish Aviation Ltd, British Aerospace PLC, British
Manufacturer(s): Aerospace (Commercial Aircraft) Ltd, British Aerospace Regional Aircraft Ltd,
Fristen: Jetstream Aircraft Ltd, British Aerospace (Operations) Ltd.
Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten HP 137 Jetstream MK 1, Jetstream Series 200, 3100 and 3200 aeroplanes, all
Applicability:
EASA Airworthiness Directive. Models, all serial numbers.
------------------------------ DRINGENDE LUFTTÜCHTIGKEITSANWEISUNG ------------------------------ BAE Systems have been notified by the main landing gear (MLG) radius
rod manufacturer, APPH Ltd, that a batch of incorrectly manufactured
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der Buffer Springs (part number 184818) has been supplied to their parts
EASA Emergency AD 2009-0181-E vom 12.08.2009 distributor and maintenance- and repair organisation (MRO) facilities in
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen North America.
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 There is a risk that any radius rod fitted with one of these incorrectly
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen. manufactured Buffer Springs could jam in an unlocked position. This
condition, if not corrected, could result in MLG collapse and consequent
Rechtsbehelfsbelehrung: Reason:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
injury to occupants of the aeroplane. EASA issued AD 2009-0121-E to
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. require the replacement of the affected radius rods.
LTAs werden auch im Internet unter http://www.lba.de publiziert BAE Systems (Operations) Ltd Alert Service Bulletin (ASB) 32-A-JA090640
*** Revision 2 (the ASB) has now been issued, which identifies an additional
seven affected radius rods by serial number (s/n).
For the reasons described above, this AD retains the requirements of AD
2009-0121-E, which is superseded, and expands the applicability to include
the replacement of the additional units.
Effective Date: 14 August 2009
EASA Form 111 Page 1/2
(LTA-Nr.: D-2009-158 vom 10.06.2009) Aktenzeichen: (01)T231-502.1/D-2009-158R1 Seite 1 von 1
EASA AD No : 2009-0181-E
Required as indicated, unless accomplished previously: Lufttüchtigkeitsanweisung
(1) Before next flight after the effective date of this AD, determine whether an LTA-Nr.: D-2009-182R1
affected radius rod is installed on the aeroplane, as identified by s/n in ersetzt: D-2009-182
paragraph 2.B of the ASB. Luftfahrt-Bundesamt
Required Action(s)
Datum der Bekanntgabe: 12.08.2009
(2) If one of the affected radius rods is found to be installed, before further
and Compliance flight, replace it with a serviceable unit. Muster: AD der ausländischen Behörde:
Time(s): AGUSTA / EUROCOPTER / EUROCOPTER EASA Emergency AD 2009-0179-E vom 11.08.2009
(3) After the effective date of this AD, do not install any of the affected radius
DEUTSCHLAND / SIKORSKY
rods (as identified by s/n in the ASB) on an aeroplane, unless it has been
sent to an authorised overhaul agency for inspection and rectification, if
necessary, and marking in accordance with APPH Service Bulletin (SB) Agusta
1847-32-14 and/or 1862-32-14, as applicable. A109 / AB139 / AW139
BAE Systems (Operations) Limited ASB 32-A-JA090640 Revision 2, dated Eurocopter
11 August 2009.
AS332 / AS350 / AS355 / AS365 / SA365 /
Ref. Publications: APPH Ltd SB 1847-32-14 and SB 1862-32-14, both dated June 2009. EC155 / EC225
The use of later approved revisions of these documents is acceptable for
compliance with the requirements of this AD. Eurocopter Deutschland
EC135 / MBB-BK 117
1. If requested and appropriately substantiated, EASA can approve
Alternative Methods of Compliance for this AD.
Sikorsky
2. The safety assessment has requested not to implement the full S-61
consultation process and an immediate publication and notification.
Geräte-Nr.: Technische Mitteilungen des Herstellers:
3. Enquiries regarding this AD should be referred to the Airworthiness 3043, 3045, 3048, 3049, 3051, 3052, 3056, Goodrich Service Bulletin 42315-489-01 Revision 1
Directives, Safety Management & Research Section, Certification 3061, Breeze-Eastern Service Bulletin SB BLH-20200-504-25-01
Remarks : Directorate, EASA. E-mail ADs@easa.europa.eu.
EASA.R.002, EASA.R.005, EASA.R.006, Breeze-Eastern Service Information Letter SIL01 BLH-20200-431
4. For any question concerning the technical content of the requirements in EASA.R.008, EASA.R.009, EASA.R.010, Breeze-Eastern Service Information Letter SIL01 HK-116-5
this AD, please contact: EASA.R.146
BAE Systems (Operations) Ltd, Customer Information Department,
Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United
Betroffenes Luftfahrtgerät:
Kingdom; Telephone +44 1292 675207, Facsimile +44 1292 675704;
E-mail: RApublications@baesystems.com
AGUSTA / EUROCOPTER / EUROCOPTER DEUTSCHLAND / SIKORSKY
Agusta A109 / AB139 / AW139,
Eurocopter AS332 / AS350 / AS355 / AS365 / SA365 / EC155 / EC225,
Eurocopter Deutschland EC135 / MBB-BK 117,
Sikorsky S-61
- Baureihen: Alle
- Werk-Nrn.: Alle
-- mit installiertem LIFESAVING SYSTEMS "D-Lok Hook" der Part-Nummer
(P/N) 410-A oder 410-F (die P/N ist Teil der LOT-Nr. 208 oder 1108)
HINWEIS:
Der betroffene Lifesaving Systems "D-Lok Hook" kann an diversen Goodrich Hook Kits,
Goodrich Rescue Hoist Assemblies oder den Breeze-Eastern Rescue Hoist Assemblies
installiert sein.
Betrifft:
(ATA 25) Equipment / Furnishings - D-Lok Hook of the Rescue Hoist - Inspection / Removal from Service /
Replacement
EASA Form 111 Page 2/2
(LTA-Nr.: D-2009-182 vom 14.07.2009) Aktenzeichen: (02)T231-502.1/D-2009-182R1 Seite 1 von 2
EASA AD No.: 2009-0179-E
Maßnahmen: EASA EMERGENCY AIRWORTHINESS DIRECTIVE
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,
AD No.: 2009-0179-E
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Date: 11 August 2009
Fristen:
Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance
Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen.
with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten and of the European third countries that participate in the activities of EASA under Article 66 of
EASA Airworthiness Directive. that Regulation.
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the
------------------------------ DRINGENDE LUFTTÜCHTIGKEITSANWEISUNG ------------------------------ continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate
an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
EASA Emergency AD 2009-0179-E vom 11.08.2009 Type Approval Holders’ Names : Type/Model designations:
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 Agusta S.p.A, A109 series and AB139/AW139,
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Eurocopter, AS332, AS350 and AS355 series, EC225,
Rechtsbehelfsbelehrung: SA365, AS365 and EC155 series,
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder Eurocopter Deutschland GmbH, EC135 and MBB-BK 117,
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
Sikorsky Aircraft Corporation S-61 helicopters
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
TCDS Numbers : EASA R.002, R.005, R.006, R.008, R.009, R.010 and R.146,
DGAC France No. 159,
FAA U.S.A. 1H15.
Foreign AD : Not applicable
Supersedure : This AD supersedes EASA AD 2009-0148-E dated 09 July 2009
Equipment / Furnishings – D-Lok Hook of the Rescue Hoist –
ATA 25
Inspection / Removal from Service / Replacement
Manufacturers: Agusta S.p.A., Agusta Aerospace Corporation, American Eurocopter LLC,
Eurocopter (formerly Eurocopter France), Eurocopter Deutschland GmbH,
Eurocopter ESPANA S.A., Sikorsky Aircraft Corporation.
Applicability: Agusta S.p.A model A109 series and AB139/AW139 helicopters ,
and
Eurocopter model AS332, AS350, AS355, SA365, AS365 and EC155 series
and EC225 LP helicopters,
and
Eurocopter Deutschland GmbH model EC135 and MBB-BK 117 helicopters,
and
Sikorsky Aircraft Corporation S-61N helicopters,
all serial numbers, if equipped with Lifesaving Systems D-Lok Hooks with part
numbers (P/N) 410-A or 410-F and identified as part of lot number 208 or 1108.
Note: the rescue hoist P/N provided in the service information of the rescue
hoist system manufacturers (Goodrich or Breeze-Eastern) is for information
only. Refer to Lifesaving Systems D-Lok Hooks P/N to determine AD
applicability.
(LTA-Nr.: D-2009-182 vom 14.07.2009) Aktenzeichen: (02)T231-502.1/D-2009-182R1 Seite 2 von 2 EASA Form 111 Page 1/3
EASA AD No.: 2009-0179-E EASA AD No.: 2009-0179-E
Reason: Field reports from rescue hoist operators have noted surface irregularities and Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative
discontinuities on D-Lok Hooks supplied by Lifesaving Systems with P/N 410-A Methods of Compliance for this AD.
and 410-F. It was determined that a non-approved change in the hook
2. The safety assessment has requested not to implement the full consultation
manufacturing process, from forged material to cast material, is the cause of
process and an immediate publication and notification.
the irregularities and discontinuities found in the material.
3. Enquiries regarding this AD should be referred to the Airworthiness
This condition, if left uncorrected, could lead to the fracture of the hook.
Directives, Safety Management & Research Section, Certification
Furthermore, the new manufacturing process has not been shown to be
Directorate, EASA. E-mail: ADs@easa.europa.eu.
compliant with the applicable regulations.
4. For any question concerning the technical content of the requirements in
EASA AD 2009-0124 was issued as an emergency measure to mandate visual
this AD, please contact:
inspection and replacement, as applicable, of D-Lok Hooks supplied by
Lifesaving System with P/N 410-A and 410-F and installed on certain Goodrich Goodrich Corporation , Sensors and Integrated Systems
Corporation hook kits or rescue hoist assemblies. 1550 S. Valley Vista Drive, Diamond Bar, California
United States of America
It has been later discovered that the same Lifesaving Systems D-Lok Hooks
Tel: +1 909 569-0210 ; Fax: +1 909 569-0387.
P/N are also installed on Breeze-Eastern Corporation rescue hoist assemblies.
Goodrich Corporation , Sensors and Integrated Systems
EASA AD 2009-0148-E, which superseded EASA AD 2009-0124, required
Saint-Ouen l'Aumône
inspection of Goodrich and Breeze-Eastern rescue hoist assemblies and, if the
13 Avenue de l'Eguillette BP 7186
affected D-Lok Hooks were found installed, their removal from service or
Cergy-Pontoise, Val d'Oise 95056 - France
replacement with serviceable parts.
Tel: +33 (0) 1 3432 6781 ; Fax: +33 (0) 1 3432 6323.
This AD, superseding EASA AD 2009-0148-E and keeping its requirements,
Breeze-Eastern Corporation
reduces the AD applicability and requires returning the cast hooks to Goodrich
700 Liberty Avenue
or Breeze-Eastern, as applicable, after removal.
Union, New Jersey 07083-8198 USA
Ph.: +1 (908) 686-4000, Ext. 3897, or 3890.
Effective Date: 12 August 2009 1-800-929-1919 (Toll-Free US and Canada only)
Fax: +1 (908) 688-6495
Required Action(s) Required as indicated, unless previously accomplished: E-Mail: customerservice@breeze-eastern.com .
and Compliance
(1) Before the next hoist operation carried out after 11 July 2009 (effective
Time(s):
date of EASA AD 2009-0148-E) inspect the rescue hoist assembly and, if a
Lifesaving Systems D-Lok Hook with P/N 410-A or 410-F and identified as
part of lot number 208 or 1108 (cast hook) is found installed, perform a
visual inspection in accordance with the applicable instructions of the
rescue hoist system manufacturer (Goodrich or Breeze-Eastern),
depending on the helicopter type. If the hook does not pass the visual
inspection, any further operation using the hook is prohibited.
The inspections and relevant corrective actions carried out, before 11 July
2009 (effective date of EASA AD 2009-0148-E), in accordance with
paragraph (1) or (3) of EASA AD 2009-0124 are acceptable to comply with
paragraph (1) of this AD.
Note: Only the visual inspection criteria of the referenced Goodrich and
Breeze-Eastern publications are applicable. Required Actions and
Compliance Times are as described in this AD section.
(2) After the effective date of this AD replace the cast hook with a serviceable
part to continue hoist operations and return the removed parts to Goodrich
or Breeze-Eastern, as applicable.
(3) After 11 July 2009 (effective date of EASA AD 2009-0148-E), do not install
a D-Lok Hook with P/N 410-A or 410-F and identified as part of lot number
208 or 1108 on any helicopter.
Ref. Publications: Goodrich Service Bulletin 42315-489-01 revision 1,
Breeze-Eastern Corporation Service Information Letter SIL01 BLH-20200-431
original release,
Breeze-Eastern Corporation Service Bulletin SB BLH-20200-504-25-01
original release,
Breeze-Eastern Corporation Service Information Letter SIL01 HK-116-5
original release.
EASA Form 111 Page 2/3 EASA Form 111 Page 3/3
