Nachrichten für Luftfahrer 2007 Teil II (weicht ggf. von Druckversion ab)
D-2007-331
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2007-332
Applicability: AIRBUS aircraft A330-200, A330-300, A340-200 and A340-
300 series, all certified models, all serial numbers, except Luftfahrt-Bundesamt
those on which both AIRBUS modifications 55656 and Datum der Bekanntgabe: 08.11.2007
55657 have been embodied in production or AIRBUS Muster: Thielert Aircraft Engines AD der ausländischen Behörde:
Service Bulletin (SB) A330-25-3316 or SB A340-25-4277 TAE125 EASA AD 2007-0232 vom 23.08.2007
has been embodied in service.
Geräte-Nr.: Technische Mitteilungen des Herstellers:
AIRBUS aircraft A340-500 and A340-600 series, all certified 4631, EASA.E.055 Thielert Service Bulletin TM TAE 125-0016
models, all serial numbers, except those on which AIRBUS Thielert Service Bulletin TM TAE 125-0016 Revision 1
modification 55656 has been embodied in production or
AIRBUS SB A340-25-5128 has been embodied in service. Betroffenes Luftfahrtgerät:
Recommendation: At the next slide raft overhaul or within 36 months after the Thielert Aircraft Engines
issue date of this SIN, whichever occurs later, install the TAE125
placard on passenger/crew doors 1 and 4 and emergency exit
door 3 (Type 1 only), RH and LH sides of the fuselage in - Baureihen: TAE125-01
accordance with instructions given in AIRBUS SB A330-25-
3316 or SB A340-25-4277 or SB A340-25-5128. - Werk-Nrn.: ab Seriennummer (S/N) 02-01-1018
Betrifft:
Contact: For further information contact the Airworthiness Directives Möglicher Ausfall des Triebwerks im Fluge durch Ausfall der Schmierölförderpumpe infolge angesaugter
Focal Point, Certification Directorate, EASA. Fremdkörper, die in den Schmierölkreislauf gelangt sind.
E-mail: ADs@easa.europa.eu.
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
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 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 2007-0232 vom 23.08.2007
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
***
2/2
Aktenzeichen: (10)T23-502.1/D-2007-332 Seite 1 von 1
EASA AIRWORTHINESS DIRECTIVE Compliance Required as indicated, unless accomplished previously:
Within the next 50 flight hours after the effective date of this directive, but not
later than 31 October 2007, whichever occurs first, modify the engine oil
system in accordance with the instructions of Thielert Aircraft Engines TM/SB
AD No.: 2007-0232 TAE 125-0016, initial issue dated 19 September 2006 or Revision 1 dated 15
June 2007.
Ref. Publications: Thielert Service Bulletin TM TAE 125-0016, Initial Issue or Revision 1 or later
Date: 23 August 2007 approved revisions.
Remarks: 1. If requested and appropriately substantiated the responsible EASA
manager for the related product has the authority to accept Alternative
Methods of Compliance (AMOCs) for this AD.
Type Approval Holder’s Name: Type/Model designation(s):
2. This AD was posted on 08 August 2007 as PAD 07-137 for consultation
until 22 August 2007. No comments were received during the consultation
Thielert Aircraft Engines TAE125-01 engines period.
3. Enquiries regarding this AD should be referred to the AD Focal Point -
TCDS Numbers: EASA E.055 Certification Directorate, EASA. E-mail: ADs@easa.europa.eu
Foreign AD: Not applicable 4. For any questions concerning the content of this AD, please contact:
Thielert Aircraft Engines
Platanenstraße 14
Supersedure: None D-09350 Lichtenstein, Germany
Telephone +49-37204-696-0; Fax +49-37204-696-55;
E-mail info@centurion-engines.com
ATA 79 Engine Oil System - Catchtank (Sump) Filter Adaptor - Installation
Manufacturer: Thielert Aircraft Engines
Applicability: TAE125-01 engines, all serial numbers (s/n), up to and including s/n 02-01-
1018.
These engines are known to be installed on, but not limited to, Cessna 172
and (Reims-built) F172 series (EASA STC Nr. EASA.A.S.01527); Piper PA-28
series (EASA STC Nr. EASA.A.S.01632), APEX (Robin) DR 400 series (EASA
STC Nr. EASA.A.S.01380); and Diamond DA40 and DA42 series aircraft.
Reason: An in-flight engine shutdown incident was reported on an aircraft equipped
with a TAE125-01 engine. This was found to be mainly the result of a
blockage of the scavenge oil gear pump due to a broken axial bearing of the
turbocharger. The broken parts were sucked into the oil pump and caused a
seizure. With the pump inoperative, the oil separator overfilled, causing the
engine oil to escape via the breather vent line. This caused a loss of oil that
resulted in the engine overheating and subsequent shutdown. Thielert, the
engine TC holder, has developed a filter adaptor for the Oil Catchtank (Sump)
that is designed to prevent foreign objects from entering into the scavenge
pump, minimising the chance of such an incident recurring.
For the reasons stated above, this Airworthiness Directive (AD) requires the
modification of all affected TAE125-01 engines by installing filter adaptor
between the Oil Catchtank and the hose leading to the dual stage oil pump.
Effective Date: 06 September 2007
1/2 2/2
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2007-333
Luftfahrt-Bundesamt AGÊNCIA NACIONAL DE AVIAÇÃO CIVIL – BRAZIL
Datum der Bekanntgabe: 08.11.2007
Muster: Embraer (Brasilien) AD der ausländischen Behörde:
ERJ-190 ANAC BAD 2007-08-04 Amdt. 39-1199 vom 27.08.2007 BRAZILIAN AIRWORTHINESS DIRECTIVE
Geräte-Nr.: Technische Mitteilungen des Herstellers:
EASA.IM.A.071 Embraer Service Bulletin No. 190-34-0009 AD No.: 2007-08-04 Effective Date: 27 Aug. 2007
The following Brazilian Airworthiness Directive (AD), issued by the Agência Nacional de Aviação Civil
(ANAC) in accordance with provisions of Chapter IV, Title III of Código Brasileiro de Aeronáutica - Law No.
Betroffenes Luftfahrtgerät: 7,565 dated 19 December 1986 - and Regulamento Brasileiro de Homologação Aeronáutica (RBHA) 39, applies to
all aircraft registered in the Registro Aeronáutico Brasileiro. No person may operate an aircraft to which
Embraer (Brasilien) this AD applies, unless it has previously complied with the requirements established herein.
ERJ-190
AD No. 2007-08-04 - EMBRAER - Amendment 39-1199.
- Baureihen: ERJ-190( )
APPLICABILITY:
- Werk-Nrn.: Alle This Airworthiness Directive is applicable to all Embraer ERJ-190( ) aircraft models in
operation.
Betrifft:
Anzeige fehlerhafter Navigationsdaten auf beiden ''Primary Flight Displays'' ohne Warnung an die Flug- CANCELLATION / REVISION:
besatzung durch technische Probleme mit den ''Inertial Reference Units (IRU)''.
Not applicable.
Maßnahmen: REASON:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten ANAC
Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen. It has been found that the implementation of the Inertial Reference Units (IRU) on the
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, ERJ-190 may lead, in certain degraded modes, to an erroneous Flight Path Angle (FPA) indication on
vollständig und innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchge- both Primary Flight Displays, with no alert to the flight crew. On the ERJ-190, FPA is considered as
führt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung important as pitch and bank angle for piloting purposes.
bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Since this condition affects flight safety, a corrective action is required. Thus, sufficient
Fristen: reason exists to request compliance with this AD in the indicated time limit.
Alle anzuwendenden Fristen sind der oben genannten ANAC Airworthiness Directive zu entnehmen.
REQUIRED ACTION:
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
ANAC Airworthiness Directive. Removal of some wiring connections in the electrical connectors of both Inertial
Reference Units.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
ANAC BAD 2007-08-04 Amdt. 39-1199 vom 27.08.2007 COMPLIANCE:
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 Required as indicated below, unless already accomplished.
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. Within the next 18 months after the effective date of this AD, remove the wiring
Rechtsbehelfsbelehrung:
connections from pins 51 and 52 in the electrical connectors of both Inertial Reference Units.
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. The detailed instructions and procedures to accomplish this AD are described in the
Embraer Service Bulletin No. 190-34-0009 original issue, or further revisions approved by the ANAC.
LTAs werden auch im Internet unter http://www.lba.de publiziert
*** 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
Aktenzeichen: (01)T23-502.1/D-2007-333 Seite 1 von 1
Form F-900-04E
CONTINUATION OF AD No.: 2007-08-04 - AMENDMENT 39-1199 PAGE No.: 2/2
For acquisition, contact:
Lufttüchtigkeitsanweisung
National Civil Aviation Agency (ANAC)
Publications Branch LTA-Nr.: D-2007-334
R. Santa Luzia, 651, 2º Mezanino, Centro
Fax: 55 (21) 3814-6929 Luftfahrt-Bundesamt
20030-040 – Rio de Janeiro - RJ, BRAZIL.
Datum der Bekanntgabe: 12.11.2007
E-mail: publicacoes@anac.gov.br Muster: Pratt & Whitney AD der ausländischen Behörde:
JT9D FAA AD 2007-17-21 Amdt. 39-15180
APPROVAL:
Geräte-Nr.: Technische Mitteilungen des Herstellers:
CLÁUDIO PASSOS SIMÃO 6311 Pratt & Whitney Alert Service Bulletin JT9D-7R4-A72-596 vom
General Manager 15.09.2005
GGCP
Betroffenes Luftfahrtgerät:
MILTON ZUANAZZI Pratt & Whitney
Director-President JT9D
ANAC
- Baureihen: JT9D-7R4G2, -7R4E1, -7R4E4 und -7R4H1
NOTE: Original in Portuguese language signed and available in the files of the Aeronautical Products - Werk-Nrn.: Alle Triebwerke dieser Baureihen mit ''Reduced Cooling Flow Vane Assemblies'' mit den
Certification Branch (GGCP) of the National Civil Aviation Agency (ANAC). Hersteller-Teilenummern (P/N's) 797282, 796972, 800082, 800072, 803182, 803282 und
822582, installiert in 2. Stufe Hochdruckturbine ''Vane Cluster Assemblies'' mit den P/N's
797592, 797372, 799872, 799782 und 822572.
Betrifft:
Möglicher Triebwerksausfall im Fluge durch Überhintzungsschäden an der Luftdichtung der 2. Stufe der
Hochdruckturbine durch mangelhafte Kühlluftzuführung.
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA
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 FAA Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
FAA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2007-17-21 Amdt. 39-15180
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
***
Aktenzeichen: (10)T23-502.1/D-2007-334 Seite 1 von 1
Form F-900-04E
[Federal Register: August 24, 2007 (Volume 72, Number 164)] SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a
[Rules and Regulations] proposed AD. The proposed AD applies to PW JT9D-7R4E1, -7R4E4, -7R4G2, and -7R4H1
[Page 48549-48551] turbofan engines. We published the proposed AD in the Federal Register on February 2, 2007 (72 FR
From the Federal Register Online via GPO Access [wais.access.gpo.gov] 4964). That action proposed to require removal of reduced cooling flow 2nd stage HPT vane
[DOCID:fr24au07-3] assemblies. It also proposed to require a visual and an FPI of the 2nd stage HPT air seal assembly.
–––––––––––––––––––––––––––––––––– Examining the AD Docket
DEPARTMENT OF TRANSPORTATION You may examine the AD docket on the Internet at http://dms.dot.gov; or in person at the Docket
Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The
Federal Aviation Administration AD docket contains the NPRM, the regulatory evaluation, any comments received, and other
information. The street address for the Docket Operations office (telephone (800) 647-5527) is
14 CFR Part 39 provided in the ADDRESSES section. Comments will be available in the AD docket shortly after
receipt.
[Docket No. FAA-2006-23742; Directorate Identifier 2005-NE-53-AD; Amendment 39-15180;
AD 2007-17-21] Comments
RIN 2120-AA64 We provided the public the opportunity to participate in the development of this AD. We have
considered the comments received.
Airworthiness Directives; Pratt & Whitney (PW) JT9D-7R4 Series Turbofan Engines
Revise the Cost Impact
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
FEDEX requests that we revise the estimated cost impact to implement the AD because they
ACTION: Final rule. believe that the actual cost of modification (according to PW Alert Service Bulletin (ASB) JT9D-
7R4-A72-596, dated September 15, 2005) for one set of HPT 2nd stage vane assemblies will be
–––––––––––––––––––––––––––––––––– approximately $23,000, instead of $5,400 projected by the proposed AD. We do not agree. We
provided the estimated material cost of $5,400 per engine from the engine manufacturer in the Costs
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for PW JT9D-7R4 series of Compliance section in the proposed AD. Parts included new 2nd stage HPT vane covers, part
turbofan engines. This AD requires removing reduced cooling flow 2nd stage high pressure turbine number (P/N) 822734, and rivets, P/N ST1219-213, that are required to modify the 2nd stage HPT
(HPT) vane assemblies, part numbers (P/Ns) 797282, 796972, 800082, 800072, 803182, 803282, and vane cluster assemblies, as specified in ASB JT9D-7R4-A72-596, dated September 15, 2005.
822582, installed in 2nd stage HPT vane cluster assemblies P/Ns 797592, 797372, 799872, 799782, However, based on latest pricing information in the PW spare parts price catalog, we increased the
and 822572. It also requires a visual and a fluorescent penetrant inspection (FPI) of the 2nd stage estimated material cost to $6,700. We also estimate that it will take about 65.5 work-hours per engine
HPT air seal assembly, P/N 815097. This AD results from a report of an uncontained failure of the to perform the actions, and that the average labor rate is $80 per work-hour. Based on these figures,
2nd stage HPT air seal assembly, caused by the air seal assembly brace disengaging from the air seal, we estimate the total cost of the AD to be $11,940 per engine.
due to insufficient cooling air flow. We are issuing this AD to prevent uncontained failure of the 2nd
stage HPT air seal assembly, leading to engine in-flight shutdown and damage to the airplane. Revise the Applicability Section
DATES: This AD becomes effective September 28, 2007. The Director of the Federal Register Boeing Company asks that we revise paragraph (c) of the AD to remove the reference to the
approved the incorporation by reference of certain publications listed in the regulations as of Boeing model 747-200B, -200C, -200F, and -300 airplanes. Boeing states that the JT9D-7R4E1, -
September 28, 2007. 7R4E4, and -7R4H1 are not used on any model Boeing 747 and the description implies that these
engines may be installed on the Boeing 747 airplane. We partially agree. We removed the letter
ADDRESSES: You can get the service information identified in this AD from Pratt & Whitney, 400 designations for the 747-200 series airplanes. However, we do not agree that the airplane listing in
Main St., East Hartford, CT 06108; telephone (860) 565-8770; fax (860) 565-4503. paragraph (c) implies that the JT9D-7R4E1, -7R4E4, and -7R4H1 engines may be installed on the
You may examine the AD docket on the Internet at http://dms.dot.gov or at the U.S. Department Boeing 747. The airplane references in paragraph (c) are informative only. The Type Certificate Data
of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 Sheet for an airplane specifies the engines that are installed on the airplane, not the applicability
New Jersey Avenue, SE., Washington, DC 20590. paragraph of an AD.
PW asks that we revise the Applicability section to clarify the affected engine models. They also
FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine request that we add the following aircraft to the list of airplanes that can have these engines installed:
Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Boeing 767-200, Airbus A300-600, and A310-300.
Burlington, MA 01803; telephone (781) 238-7758, fax (781) 238-7199. We partially agree and revised the Applicability section of the AD to add Boeing 767-200, and
Airbus A300-600 and A310-300 airplane models to paragraph (c) of the AD. We do not agree that we
1 2
need to clarify the engine models with Pratt & Whitney internal model designation. We specify the Costs of Compliance
affected engines by the model designations specified in the Type Certificate Data Sheet for the
engine. We estimate that this proposed AD would affect 85 PW JT9D-7R4 series turbofan engines
installed on airplanes U.S. registry. We also estimate that it will take about 65.5 work-hours per
Revise Paragraph (f) of the Compliance Section engine to perform the actions, and that the average labor rate is $80 per work-hour. Required parts
will cost about $6,700 per engine. Based on these figures, we estimate the total cost of the AD to U.S.
PW asks that we revise paragraph (f) of the Compliance section to delete the specific lenticular operators to be $1,014,900.
seal part number reference, as there are other lenticular seal part numbers in the field that will also
require visual and FPI inspections at the next HPT module exposure. We partially agree. The specific Authority for This Rulemaking
lenticular seal part number should be removed from paragraph (f) of the Compliance section of the
AD because there are other lenticular seal part numbers in the field that will also require inspections. Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
However, to prevent further delay in addressing the unsafe condition, we are issuing this AD with the Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
specific lenticular seal part number listed. Removal of the part number will expand the number of Programs, describes in more detail the scope of the Agency's authority.
parts requiring inspection and we must give the public an opportunity to comment on this change We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III,
before we can incorporate it. We will supersede this AD to remove the lenticular seal part number. 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,
List Required Lenticular Seal Inspections 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
PW asks that we revise paragraph (f) of the Compliance section to list all of the specific to exist or develop on products identified in this rulemaking action.
inspections required for the lenticular seal. We agree and listed each inspection procedure in the PW
engine manual required for the lenticular seal. We also changed the paragraph to (g). Regulatory Findings
Revise Paragraph (g) of the Compliance Section 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
PW also asks that we revise paragraph (g) of the Compliance section to reference the associated national government and the States, or on the distribution of power and responsibilities among the
2nd stage HPT vane cluster assemblies (higher level assembly) that have reduced cooling flow 2nd various levels of government.
stage HPT vane assemblies installed, because airlines may not recognize individual 2nd stage vane For the reasons discussed above, I certify that this AD:
assemblies. We agree. We revised paragraph (g) of the Compliance section to state the following: ''At (1) Is not a ''significant regulatory action'' under Executive Order 12866;
the next HPT module exposure, remove reduced cooling flow 2nd stage HPT vane assemblies, P/Ns (2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034,
797282, 796972, 800082, 800072, 803182, 803282, and 822582, installed in 2nd stage HPT vane February 26, 1979); and
cluster assemblies, P/Ns 797592, 797372, 799872, 799782, and 822572.'' We also designated the (3) Will not have a significant economic impact, positive or negative, on a substantial number of
paragraph as (f). small entities under the criteria of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
Correct Errors and Remove Duplicate P/N Reference placed it in the AD Docket. You may get a copy of this summary at the address listed under
ADDRESSES.
Boeing Company asks that we correct typographical errors for the engine designations in
paragraph (c) in the Applicability section. Boeing states that the JT9D-74R4E1, -74R4E4, -74R4G2, List of Subjects in 14 CFR Part 39
and -74R4H1 should be JT9D-7R4E1, -7R4E4, -7R4G2, and -7R4H1, respectively.
Boeing also asks that we revise paragraph (g) in the Compliance section to remove a duplicate Air transportation, Aircraft, Aviation safety, Safety.
reference to part number 803182. We agree and corrected the Applicability section and the duplicate
P/N reference in paragraph (g). Adoption of the Amendment
Conclusion Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation
Administration amends 14 CFR part 39 as follows:
We have carefully reviewed the available data, including the comments received, and determined
that air safety and the public interest require adopting the AD with the changes described previously. PART 39–AIRWORTHINESS DIRECTIVES
We have determined that these changes will neither increase the economic burden on any operator
nor increase the scope of the AD. 1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
3 4
§ 39.13 [Amended] AIRWORTHINESS DIRECTIVE
FAA
2. The FAA amends § 39.13 by adding the following new airworthiness directive: Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html
2007-17-21 Pratt & Whitney: Amendment 39-15180. Docket No. FAA-2006-23742; Directorate
Identifier 2005-NE-53-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective September 28, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Pratt & Whitney (PW) JT9D-7R4G2, -7R4E1, -7R4E4, and -7R4H1
series turbofan engines. These engines are installed on, but not limited to, Boeing 747-200, -300,
767-200, and Airbus A300-600 and A310-300 series airplanes.
Unsafe Condition
(d) This AD results from a report of an uncontained failure of the 2nd stage high pressure turbine
(HPT) air seal assembly, caused by the air seal assembly brace disengaging from the air seal, due to
insufficient cooling air flow. We are issuing this AD to prevent uncontained failure of the 2nd stage
HPT air seal assembly, leading to engine in-flight shutdown and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this AD performed at the next HPT
module exposure after the effective date of this AD, unless the actions have already been done.
(f) At the next HPT module exposure, remove reduced cooling flow 2nd stage HPT vane
assemblies part numbers (P/Ns): 797282, 796972, 800082, 800072, 803182, 803282, and 822582,
installed in 2nd stage HPT vane cluster assemblies: P/Ns 797592, 797372, 799872, 799782, and
822572.
(g) For 2nd stage HPT air seals that have operated in an engine with reduced cooling flow HPT
vane assemblies, at the next HPT module exposure do the following:
(1) Perform a onetime visual inspection of the 2nd stage HPT air seal assembly, P/N 815097,
using instructions in JT9D-7R4 engine manual, Section 72-51-22, Inspection/Check-01, paragraphs
1.D.(1), 1.D.(4), and 1.D.(6).
(2) Perform a fluorescent penetrant inspection (FPI) of the 2nd stage HPT air seal assembly for
cracks, using instructions in JT9D-7R4 engine manual, Section 71-51-00, Inspection/Check-03.
5 6
Definition Lufttüchtigkeitsanweisung
LTA-Nr.: D-2007-335
(h) For the purpose of this AD, an HPT module exposure is defined as removing the 1st stage
HPT rotor or the 2nd stage HPT rotor from the HPT case. Luftfahrt-Bundesamt
Datum der Bekanntgabe: 13.11.2007
Alternative Methods of Compliance Muster: Avions Pierre Robin / Apex AD der ausländischen Behörde:
alle gemäß EASA-AD EASA 2007-0210 vom 06.08.2007
(i) The Manager, Engine Certification Office, has the authority to approve alternative methods of Geräte-Nr.: Technische Mitteilungen des Herstellers:
compliance for this AD if requested using the procedures found in 14 CFR 39.19. 676, 741, 1001, 1013, 1016, 1075, DGAC APEX Service Bulletin No. 060903
TCDS 178
Related Information
Betroffenes Luftfahrtgerät:
(j) Pratt & Whitney Alert Service Bulletin JT9D-7R4-A72-596, dated September 15, 2005,
contains information for modifying the reduced cooling flow 2nd stage HPT vane assemblies. Avions Pierre Robin / Apex
alle gemäß EASA-AD
Issued in Burlington, Massachusetts, on August 17, 2007. - Baureihen: - alle Baureihen der Luftfahrzeugmuster DR220, DR221, DR200, DR250, DR253, R3000
Peter A. White, und ATL
Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. - alle R1180T und R1180TD
[FR Doc. E7-16665 Filed 8-23-07; 8:45 am] - alle DR 300 Baureihen sowie DR315, DR340, DR360 und DR380
- alle DR 400 Baureihen, ausgenommen DR400/500, DR400/RP und DR400/200R
- Werk-Nrn.: alle, ausgestattet mit elektrischer Kraftstoffpumpe P/N 52.88.03.100 oder P/N 52.11.69.000
gemäß den Angaben der EASA-AD
Betrifft:
Kraftstoffanlage (''Fuel – Fuel Pump Electrical Grounding – Modification'')
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
***
7
Aktenzeichen: (01)T231-502.1/D-2007-335 Seite 1 von 1
D-2007-335 D-2007-335
EASA AIRWORTHINESS DIRECTIVE Compliance: Within the next 50 flight hours after the effective date of this AD, unless already
accomplished, modify the aircraft electrical fuel pump support to install the
bonding wire between the electric fuel pump and the bayonet connector support
as indicated in the accomplishment instructions of the APEX SB No 060903
original issue or later approved issue.
AD No: 2007- 0210
Ref. Publications: APEX SB n°060903 original issue or later approved issue.
Remarks: 1. If requested and appropriately substantiated the responsible EASA
Date: 06 August 2007 manager for the related product has the authority to accept Alternative
Methods of Compliance (AMOCs) for this AD.
No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the
2. This AD was posted for consultation on 06 July 2007 as PAD 07-116 until
requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry. 20 July 2007. No comments were received during the consultation period.
3. Enquiries regarding this AD should be referred to the AD Focal Point -
Type Approval Holder’s Name : Type/Model designation(s): Certification Directorate, EASA; E-mail: ADs@easa.europa.eu .
APEX AIRCRAFT (see applicability section) 4. For any questions concerning the technical content of the requirements in
this AD, please contact:
APEX AIRCRAFT, Bureau de Navigabilité, 1 route de Troyes
TCDS Number: DGAC France No.111, 115, 172, 178, 100, 131, 121 21121 Darois FRANCE;
Tel : + 33 380 35 65 10 – Fax : + 33 38035 6515
Foreign AD : Not applicable e-mail: airworthiness@apex-aircraft.com
Supersedure: Not applicable
ATA 28 Fuel – Fuel Pump Electrical Grounding – Modification
Centre Est Aéronautique, Avions Pierre Robin, Constructions Aéronautiques de
Manufacturers:
Bourgogne, APEX Industries.
Applicability: All DR220 series and DR221series aircraft models;
All DR200 and all DR250 series aircraft models;
All DR253 series aircraft models;
All R3000 series aircraft models;
All ATL series aircraft models;
All R1180T and R1180TD aircraft;
All DR300 series aircraft models, DR315, DR340, DR360 and DR380;
All DR400 series aircraft models, except DR400/500, DR400/RP and
DR400/200R;
if equipped with electrical fuel pump Part Number (P/N) 52.88.03.100 or P/N
52.11.69.000 with unshielded power supply cable.
Reason: Several electrical fuel pump malfunctions have been reported to APEX Aircraft.
A modification of the pump feeder cable made by the fuel pump manufacturer
revealed to be cause of malfunctions. Braiding of the feeder cable which
performs the grounding of the electric fuel pump was simply suppressed.
Consequently, if left uncorrected, after a failure of the mechanical pump, the
electrical fuel pump may not work as a backup and this could lead to an engine
stoppage.
For the reasons stated above, this Airworthiness Directive (AD) requires
modification of the electric fuel pump to restore its electrical grounding.
Effective Date: 20 August 2007
1/2 2/2
D-2007-336
Lufttüchtigkeitsanweisung AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2007-336 FAA
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/
Luftfahrt-Bundesamt www.gpoaccess.gov/fr/advanced.html
Datum der Bekanntgabe: 13.11.2007
Muster: Enstrom AD der ausländischen Behörde: 2007-11-02 Enstrom Helicopter Company: Amendment 39-15059. Docket No. FAA-2006-26771;
ENSTROM F-28 FAA AD 2007-11-02 Amdt. 39-15059
Directorate Identifier 2005-SW-07-AD.
Geräte-Nr.: Technische Mitteilungen des Herstellers:
3041 Enstrom Service Directive Bulletin No. 0096 vom 10.09.2003 Applicability: Model F-28A, F-28C, and F-28F helicopters, excluding serial number (S/N) 816
Enstrom Service Directive Bulletin No. T-019 vom 10.09.2003 and subsequent; Model 280, 280C, 280F, and 280FX helicopters, excluding S/N 2100 and
Enstrom Service Information Letter No. T-019 vom 09.12.2003
Entrom Service Information Letter No. 0156 vom 09.12.2003
subsequent; and Model TH-28, 480, and 480B helicopters, excluding S/N 5058 and subsequent,
certificated in any category.
Betroffenes Luftfahrtgerät:
Compliance: Required as indicated, unless accomplished previously.
Enstrom To detect corrosion and prevent failure of a main rotor push-pull control rod (push-pull rod), and
ENSTROM F-28 subsequent loss of control of the helicopter, accomplish the following:
- Baureihen: F-28A, F-28C und F-28F
- Werk-Nrn.: alle, ausgenommen 816 und nachfolgende
(a) Within 10 hours time-in-service (TIS) or at the next annual inspection, whichever occurs first,
review the helicopter maintenance records and determine the date that each push-pull rod, part
280, 280C, 280F und 280FX number (P/N) 28-16253–all dash numbers (for Model F-28A, F-28C, F-28F, 280, 280C, 280F, and
- Werk-Nrn.: alle, ausgenommen 2100 und nachfolgende 280FX helicopters) and P/N 4140532–all dash numbers (for Model TH-28, 480, and 480B
helicopters), was installed. If the date cannot be determined from the maintenance records, use the
TH-28, 480 und 480B
- Werk-Nrn.: alle, ausgenommen 5058 und nachfolgende
''Date MFD'', which is located on the helicopter data plate, as the installation date for the push-pull
rod.
- Werk-Nrn.: siehe Angaben unter ''Baureihen''
(b) For Model F-28A, F-28C, F-28F, 280, 280C, 280F, and 280FX helicopters, using the
Betrifft: compliance times stated in Table 1 of this AD, visually inspect the exterior and interior of each of the
Flugsteuerung / Hauptrotorsteuerstangen (''corrosion / failure of a main rotor push-pull control rod'') three push-pull rods for corrosion severe enough to cause pitting or any moisture, paying special
attention to the area of the lower fitting, in accordance with section 5.1., INSPECTION, in Enstrom
Maßnahmen: Helicopter Corporation Service Directive Bulletin No. 0096, dated September 10, 2003 (SDB 0096).
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten AD der
ausländischen Behörde und der oben genannten Technischen Mitteilung des Herstellers zu entnehmen.
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig Table 1
und innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Helicopter models Push-pull rod service life Compliance times
Zustimmung durch das Luftfahrt-Bundesamt.
Model F–28A, F–28C, F–28F, Push-pull rod that has been Inspect within 10 hours time-in-
280, 280C, 280F, and 280FX installed for 20 or more service (TIS) or at next annual
Fristen:
Alle anzuwendenden Fristen sind der o. g. AD der ausländischen Behörde zu entnehmen. helicopters. years. inspection, whichever occurs first.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der o. g. AD der Model F–28A, F–28C, F–28F, Push-pull rod that has been Inspect within 50 hours TIS or at
ausländischen Behörde.
280, 280C, 280F, and 280FX installed for 10 or more the next annual inspection,
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen helicopters. years, but less than 20 whichever occurs first.
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
years.
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Model F–28A, F–28C, F–28F, Push-pull rod that has been Inspect before the service life of the
Rechtsbehelfsbelehrung: 280, 280C, 280F, and 280FX installed for less than 10 push-pull rod reaches 10 years since
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. helicopters. years. initial installation.
LTAs werden auch im Internet unter http://www.lba.de publiziert
*** (1) Before further flight, if corrosion without pitting is found on a push-pull rod, then repair,
reassemble, remark, and reinstall it in accordance with section 5.2., REPAIR/REASSEMBLY, in
SDB 0096.
5
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