Nachrichten für Luftfahrer 2005 Teil II (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung [Federal Register: June 14, 2005 (Volume 70, Number 113)]
LTA-Nr.: D-1979-004R5 [Rules and Regulations]
ersetzt: D-1979-004/4 [Page 34336-34339]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 19.07.2005 [DOCID:fr14jn05-10]
Muster: Teledyne Continental Motors AD der ausländischen Behörde: –––––––––––––––––––––––––––––––––––
Zündmagnete FAA AD 2005-12-06 Amdt. 39-14122
Geräte-Nr.: Technische Mitteilungen des Herstellers: DEPARTMENT OF TRANSPORTATION
-keine- TCM Mandatory Service Bulletin No. 645 vom 04.04.1994
TCM Service Bulletin No. 639 Ausgabe März 1993 Federal Aviation Administration
TCM Service Information Letter No. SIL648 vom 18.10.1994
14 CFR Part 39
Betroffenes Luftfahrtgerät:
Teledyne Continental Motors [Docket No. 93-ANE-07-AD; Amendment 39-14122; AD 2005-12-06]
Zündmagnete
RIN 2120-AA64
- Baureihen: S-20 Serie
S-1200 Serie
Airworthiness Directives; Teledyne Continental Motors (Formerly Bendix) S-20, S-1200, D-
D-2000 Serie
D-3000 Serie 2000, and D-3000 Series Magnetos
die mit einer Schnappkupplung ausgerüstet sind
AGENCY: Federal Aviation Administration (FAA), DOT.
- Werk-Nrn.: Alle
ACTION: Final rule.
Betrifft:
Zündmagnet, Schnappkupplung (magnetos, imulse couplings, ATA-Kap. 74-00-00) - Ausfall von Zünd-
magneten durch starke Verschleißerscheinungen an Teilen der Schnappkupplung - ggf. können durch –––––––––––––––––––––––––––––––––––
diesen Fehler Betriebsstörungen und Motorausfälle eintreten.
SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Teledyne
Maßnahmen: Continental Motors (TCM) (formerly Bendix) S-20, S-1200, D-2000, and D-3000 series magnetos
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA equipped with impulse coupling assemblies. That AD currently requires replacing riveted-impulse
Airworthiness Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen. coupling assemblies and snap-ring coupling assemblies, which are worn beyond limits, with
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
vollständig und innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchge-
serviceable riveted-impulse coupling assemblies or snap-ring impulse coupling assemblies. This ad
führt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung requires a reduced inspection interval for magnetos with riveted-impulse coupling assemblies
bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt. installed on certain Lycoming engine models. This AD does not lower the inspection interval for
magnetos with snap-ring impulse coupling assemblies. This AD also limits the applicability to certain
Fristen: Lycoming engine models. This AD results from data provided by the manufacturer that shows a need
Alle anzuwendenden Fristen sind der oben genannten FAA Airworthiness Directive zu entnehmen. to reduce the inspection intervals for riveted-impulse coupling assemblies used on certain Lycoming
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
engine models. We are issuing this AD to prevent failure of the magneto impulse coupling assembly
FAA Airworthiness Directive.
and possible engine failure.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2005-12-06 Amdt. 39-14122 DATES: This AD becomes effective July 19, 2005. The Director of the Federal Register previously
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
approved the incorporation by reference of certain publications as listed in the regulations as of July
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es 18, 1996 (61 FR 29934, June 13, 1996).
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Rechtsbehelfsbelehrung: ADDRESSES: You can get the service information identified in this AD from Teledyne Continental
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.
Motors, P.O. Box 90, Mobile, AL 36601; telephone (334) 438-3411. For the Teledyne Continental
Motors Web site: Go to http://www.TCMLINK.com.
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
You may examine the AD docket at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA. You may examine the service
information, at the FAA, New England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA).
1
(LTA-Nr.: D-1979-004/4 vom 10.10.1996) Aktenzeichen: (10)T23-502.1/D-1979-004R5 Seite 1 von 1
For information on the availability of this material at NARA, call 202-741-6030, or go to: Request To Not Change From the Current AD
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
One commenter states that without the current AD, owners and operators will not have the
FOR FURTHER INFORMATION CONTACT: Jerry Robinette, Senior Aerospace Engineer, manufacturer's recommended maintenance performed, and safety will suffer.
Propulsion, Atlanta Aircraft Certification Office, FAA, Small Airplane Directorate, 1 Crown Center, We do not agree. While a small percentage of operators may not voluntarily comply with the
1895 Phoenix Blvd., Suite 450, Atlanta, GA, 30349; telephone (770) 703-6096, fax (770) 703-6097. manufacturer's recommended maintenance, we anticipate virtually all will comply. The response to
the Airworthiness Concern Sheet, Special Airworthiness Information Bulletin, and manufacturer's
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a data, indicates the AD is only needed for the Lycoming 540 series engines. This action does not
proposed airworthiness directive (AD). The proposed AD applies to TCM S-20, S-1200, D-2000, and negate the 500-hour inspection recommended by TCM. That inspection is part of the total inspection
D-3000 series magnetos equipped with impulse coupling assemblies. We published the proposed AD program to ensure the continued airworthiness of the engine. Therefore, we anticipate that safety will
in the Federal Register on December 22, 2004 (69 FR 76632). That action proposed to require: not suffer.
• An initial visual inspection of riveted-impulse coupling assemblies that have 100 or more hours
time-since-new (TSN) or time-since-last-inspection (TSLI) on the effective date of the proposed AD, Addition of Description of Magneto Model Numbering System
within 10 hours time-in-service (TIS) after the effective date of this AD, or
• An initial visual inspection of riveted-impulse coupling assemblies that have fewer than 100 To assist owners and operators, we have added the description of the magneto numbering system
hours TSN or TSLI on the effective date of the proposed AD, before accumulating 100 hours TSN or used for TCM S-20, S-1200, D-2000, and D-3000 series magnetos to the compliance section of the
TSLI, and AD.
• Repetitive inspections of riveted-impulse coupling assemblies within intervals of 100 hours
TSLI. Conclusion
• An initial visual inspection of snap-ring impulse coupling assemblies that have 450 or more
hours TSN or TSLI on the effective date of the proposed AD, within 50 hours TIS after the effective We have carefully reviewed the available data, including the comments received, and determined
date of the AD, or that air safety and the public interest require adopting the AD with the changes described previously.
• An initial visual inspection of snap-ring impulse coupling assemblies that have fewer than 450 We have determined that these changes will neither increase the economic burden on any operator
hours TSN or TSLI before accumulating 500 hours TSN or TSLI, and nor increase the scope of the AD.
• Repetitive inspections of snap-ring impulse coupling assemblies within intervals of 500 hours
TSLI. Costs of Compliance
• Replacing impulse coupling assemblies that fail the inspection.
We estimate that this AD will affect about 4,200 magnetos installed on airplanes of U.S. registry.
We also estimate that it will take about 1 work hour per magneto to perform the actions, and that the
Examining the AD Docket
average labor rate is $65 per work hour. The reduced inspection interval will require doing the
inspections about four times more often. Based on these figures, we estimate the total cost of the AD
You may examine the AD Docket (including any comments and service information), by
to U.S. operators to be $1,092,000.
appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See
ADDRESSES for the location.
Special Flight Permits Paragraph Removed
Comments
Paragraph (d) of the current AD, AD 96-12-07, contains a paragraph pertaining to special flight
permits. Even though this final rule does not contain a similar paragraph, we have made no changes
We provided the public the opportunity to participate in the development of this AD. We have
with regard to the use of special flight permits to operate the airplane to a repair facility to do the
considered the comments received.
work required by this AD. In July 2002, we published a new 14 CFR part 39 that contains a general
authority regarding special flight permits and airworthiness directives; see Docket No. FAA-2004-
Request To Not Change the Eligibility From the Current AD
8460, Amendment 39-9474 (69 FR 47998, July 22, 2002). Thus, when we now supersede ADs we
will not include a specific paragraph on special flight permits unless we want to limit the use of that
One commenter requests that we not change the eligibility from the current AD. The commenter
general authority granted in section 39.23.
states that experience has shown that the current AD is preventing failures and there is no difference
between the wear or reliability of the impulse coupling assemblies installed on one make and model
of engine, or another. Authority for This Rulemaking
We do not agree. Responses we received to the Airworthiness Concern Sheet and Special
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Airworthiness Information Bulletin from owners and operators, and the manufacturer's data, indicate
Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
that there is a significant difference in the wear and reliability of magnetos installed on Lycoming
Programs, describes in more detail the scope of the Agency's authority.
540 series engines as compared with other engines. Based on these responses, we have appropriately
We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III,
reduced the inspection interval for magnetos with riveted-impulse coupling assemblies installed on
section 44701, ''General requirements.'' Under that section, Congress charges the FAA with
Lycoming 540 series engines.
promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
2 3
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.
AIRWORTHINESS DIRECTIVE
Regulatory Findings
Aircraft Certification Service U.S. Department
of Transportation
We have determined that this AD will not have federalism implications under Executive Order Washington, DC Federal Aviation
13132. This AD will not have a substantial direct effect on the States, on the relationship between the Administration
national government and the States, or on the distribution of power and responsibilities among the We post ADs on the internet at "www.faa.gov"
The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Title 14 of the Code of Federal Regulations (14 CFR) part 39,
various levels of government. applies to an aircraft model of which our records indicate you may be the registered owner. Airworthiness Directives affect aviation safety and are regulations which require immediate
attention. You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of the Airworthiness
For the reasons discussed above, I certify that this AD: Directive (reference 14 CFR part 39, subpart 39.3).
(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, 2005-12-06 Teledyne Continental Motors: Amendment 39-14122. Docket No. 93-ANE-07-AD.
February 26, 1979); and
(3) Will not have a significant economic impact, positive or negative, on a substantial number of Effective Date
small entities under the criteria of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. (a) This AD becomes effective July 19, 2005.
You may get a copy of this summary by sending a request to us at the address listed under
ADDRESSES. Include ''AD Docket No. 93-ANE-07-AD'' in your request. Affected ADs
List of Subjects in 14 CFR Part 39 (b) This AD supersedes AD 96-12-07, Amendment 39-9649.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Applicability
Adoption of the Amendment (c) This AD applies to Teledyne Continental Motors (TCM) (formerly Bendix) magnetos that
have a magneto part number (P/N) listed in Table 1 of TCM Mandatory Service Bulletin (MSB) No.
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation MSB645, dated April 4, 1994, installed on Lycoming AEIO-540, HIO-540, IO-540, 0-540, and TIO-
Administration amends 14 CFR part 39 as follows: 540 series engines. These engines are installed on, but not limited to, airplanes manufactured by the
Cessna Aircraft Company, Maule Aerospace Technology Corporation, Mooney Aircraft Corporation,
PART 39–AIRWORTHINESS DIRECTIVES The New Piper Aircraft Inc., and Raytheon Aircraft Company (Formerly Beech Aircraft Company).
1. The authority citation for part 39 continues to read as follows: Unsafe Condition
Authority: 49 U.S.C. 106(g), 40113, 44701. (d) This AD results from data provided by the manufacturer that indicates a need to reduce the
inspection intervals for riveted-impulse coupling assemblies used on certain Lycoming engine
§ 39.13 [Amended] models. We are issuing this AD to prevent failure of the magneto impulse coupling assembly and
possible engine failure.
2. The FAA amends § 39.13 by removing Amendment 39-9649 (61 FR 29934, June 13, 1996) and by
adding a new airworthiness directive, Amendment 39-14122, to read as follows: 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.
Initial Inspections of Impulse Coupling Assemblies
(f) For all magnetos that have a P/N listed in Table 1 of TCM MSB No. MSB645, dated April 4,
1994, that have never been inspected, perform an initial inspection of the impulse coupling assembly
for wear using paragraphs 1.2 through 1.4.5 of the Detailed Instructions of TCM MSB No. MSB645,
dated April 4, 1994. Use the following Table 1 for the compliance times. Snap-ring impulse coupling
assemblies will have an ''A'' stamped in the lower-right quarter of the magneto data plate.
4 5
TABLE 1.—INITIAL INSPECTION COMPLIANCE TIMES inspection requirements specified in paragraph (i) of this AD. You can find more information on
Engine Model Type of impulse Time on impulse coupling Inspect installing a ''Shower-of-Sparks'' ignition system in TCM Service Information Letter No. SIL648,
coupling assembly assembly on the effective dated October 18, 1994.
date of this AD
Lycoming AEIO–540, (1) Riveted (i) 100 or more hours time- Within 10 hours time-in- Description of Magneto Model Numbering System
HIO–540, IO-540, 0– since-new or overhaul (TSN) service (TIS) after the
540, and TIO–540 or if the TSN is unknown. effective date of this AD. (m) To assist owners and operators, the description of the magneto numbering system used for
series engines. (ii) Fewer than 100 hours Before accumulating 100 TCM S-20, S-1200, D-2000, and D-3000 series magnetos is in the following Table 3:
TSN hours TSN.
(2) Snap ring (i) 450 or more hours TSN Within 50 hours TIS after TABLE 3.—MAGNETO NUMBERING SYSTEM
the effective date of this Code: Signifies:
AD. S or D Ignition Type (Single or Dual)
(ii) Fewer than 450 hours Before accumulating 500 6 Number of Cylinders
TSN hours TSN. L or R Direction of Rotation (Left-hand or Right-hand)
N (Not used on SC Models) Manufacturer Designation
(g) Replace any impulse coupling assembly that fails the inspection with a serviceable riveted or SC (if applicable) Short Cover Configuration
snap-ring impulse coupling assembly. Paragraphs 2 through 2.6 of the Detailed Instructions of TCM –25, –1209, or –3200 Magneto Series
MSB No. MSB645, dated April 4, 1994 contain information on replacing the impulse coupling Examples: Description:
assembly. S6LN–1209 Single type ignition, 6-cyclinder engine, left-hand rotation, TCM
(formerly Bendix), S–1200 series
(h) If you replace a snap-ring impulse coupling assembly with a riveted-impulse coupling D6RN–3200 Dual type ignition, 6-cylinder engine, right-hand rotation, TCM
assembly, strike out the ''A'' on the magneto data plate. (formerly Bendix), D–3000 series
S6LSC–25 Single type ignition, 6-cylinder engine, left-hand rotation, short cover
Repetitive Inspections of Impulse Coupling Assemblies configuration, S–20 series
(i) For all magnetos that have a P/N listed in Table 1 of TCM MSB No. MSB645, dated April 4, Alternative Methods of Compliance
1994, that have had an initial inspection as specified in paragraph (f) of this AD, perform repetitive
inspections of the impulse coupling assembly for wear using paragraphs 1.2 through 1.4.5 of the (n) The Manager, Atlanta Aircraft Certification Office, has the authority to approve alternative
Detailed Instructions of TCM MSB No. MSB645, dated April 4, 1994. Use the following Table 2 for methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19.
the compliance times. Snap-ring impulse coupling assemblies will have an ''A'' stamped in the lower-
right quarter of the magneto data plate. Related Information
TABLE 2.—REPETITIVE INSPECTION COMPLIANCE TIMES (o) TCM SB No. 639, dated March 1993, contains additional information for replacing impulse
Engine model Type of impulse Inspect coupling assemblies on a TCM magneto. TCM Service Information Letter No. SIL648, dated
coupling assembly October 18, 1994, contains information for converting an engine to a ''Shower-of-Sparks'' ignition
Lycoming AEIO–540, HIO– (1) Riveted Within 100 hours time-since- system.
540, IO–540, 0–540, and last inspection (TSLI).
TIO–540 series engines (2) Snap ring Within 500 hours TSLI. Material Incorporated by Reference
(j) Replace any impulse coupling assembly that fails the inspection with a serviceable riveted or (p) You must use Teledyne Continental Motors Mandatory Service Bulletin No. MSB645, dated
snap-ring impulse coupling assembly. Paragraphs 2 through 2.6 of the Detailed Instructions of TCM April 4, 1994 to perform the inspections and replacements required by this AD. The Director of the
MSB No. MSB645, dated April 4, 1994 contain information on replacing the impulse coupling Federal Register approved the incorporation by reference of this service bulletin as of July 18, 1996
assembly. (61 FR 29934, June 13, 1996). You can get a copy from Teledyne Continental Motors, P.O. Box 90,
Mobile, AL 36601; telephone (334) 438-3411. For the Teledyne Continental Motors Web site: Go to
(k) If you replace a snap-ring impulse coupling assembly with a riveted-impulse coupling http://www.TCMLINK.com. You can review copies at the FAA, New England Region, Office of the
assembly, strike out the ''A'' on the magneto data plate. Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and
Records Administration (NARA). For information on the availability of this material at NARA, call
Optional Terminating Action 202-741-6030, or go to:
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
(l) Installing a ''Shower-of-Sparks'' ignition system in place of a magneto system that has a
riveted-impulse coupling assembly or a snap-ring impulse coupling assembly ends the repetitive
6 7
Issued in Burlington, Massachusetts, on June 6, 2005. Lufttüchtigkeitsanweisung
Jay J. Pardee, LTA-Nr.: D-1998-310R3
Manager, Engine and Propeller Directorate, Aircraft Certification Service. ersetzt: D-1998-310R2
[FR Doc. 05-11610 Filed 6-13-05; 8:45 am]
BILLING CODE 4910-13-P
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 19.07.2005
Muster: REVO AD der ausländischen Behörde:
Lake LA-4-200 FAA AD 2005-12-02 Amdt. 39-14118
EASA AD 2005-0017 Cancellation vom 08.07.2005
Geräte-Nr.: Technische Mitteilungen des Herstellers:
1050 Revo Service Bulletin B-78 vom 03.04.1998
Betroffenes Luftfahrtgerät:
REVO
Lake LA-4-200
- Baureihen: Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P und Lake LA-4-200
- Werk-Nrn.: Alle
Betrifft:
LEITWERKE (ATA: 55): Höhenflossen-Anschlussbeschlag (Fitting P/N 2-2200-21)
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA Airworthiness
Directive (AD) und den genannten technischen Mitteilungen des Herstellers zu entnehmen. Alle erforderlichen
Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und innerhalb der
vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle Abweichungen von
den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das
Luftfahrt-Bundesamt.
Fristen:
Alle anzuwendenden Fristen sind der oben genannten FAA Airworthiness Directive (AD) zu entnehmen. Die
Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten FAA
Airworthiness Directive (AD).
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2005-12-02 Amdt. 39-14118
EASA AD 2005-0017 Cancellation vom 08.07.2005
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-1998-310R2 vom 23.06.2005) Aktenzeichen: (01)T233-502.1/D-1998-310R3 Seite 1 von 1
Actions Compliance Procedures
AIRWORTHINESS DIRECTIVE (1) For airplanes with 825 hours time-in-service Within the next 25 hours Follow Revo, Inc.
(TIS) or more on any horizontal stabilizer TIS after July 8, 2005 Service Bulletin B–78,
attachment fitting as of July 8, 2005 (the (the effective date of this dated April 3, 1998,
Aircraft Certification Service U.S. Department
effective date of this AD): AD) Repetitively replace paragraphs 2 and 3 of
of Transportation (i) Replace the horizontal stabilizer attachment any horizontal stabilizer the INSPECTION and
Washington, DC Federal Aviation fitting (part number (P/N) 2–2200–21). attachment fitting (P/N REPAIR section and
Administration (ii) If necessary, trim the horizontal stabilizer rear 2–2200–21) thereafter the APPENDIX.
We post ADs on the internet at "www.faa.gov"
The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Title 14 of the Code of Federal Regulations (14 CFR) part 39,
beam doubler flange to provide positive following paragraph
applies to an aircraft model of which our records indicate you may be the registered owner. Airworthiness Directives affect aviation safety and are regulations which require immediate
attention. You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of the Airworthiness
clearance to the fitting. (e)(3) of this AD.
Directive (reference 14 CFR part 39, subpart 39.3). (2) For airplanes with less than 825 hours TIS on Inspect within the next 25 Follow Revo, Inc.
any horizontal stabilizer attachment fitting as hours TIS after July 8, Service Bulletin B–78,
2005-12-02 Revo, Incorporated (Type Certificate 1A13 formerly held by Colonial Aircraft of July 8, 2005 (the effective date of this AD): 2005 (the effective date dated April 3, 1998,
Company, Lake Aircraft Corporation, Consolidated Aeronautics, Inc., and Global Amphibians (i) Remove the horizontal stabilizer attachment of this AD), unless INSPECTION and
LLC): Amendment 39-14118; Docket No. FAA-2005-21092; Directorate Identifier 2005-CE-20-AD. fitting (P/N 2–2200–21) from the airplane and already done. If cracks, REPAIR section and
inspect for cracks (using dye penetrant), fretting, or corrosion is the APPENDIX.
When Does This AD Become Effective? fretting, or corrosion. To take ‘‘already done’’ found, replace before
credit for this, you must have removed the further flight after the
(a) This AD becomes effective on July 8, 2005. fitting from the airplane when the inspection inspection.
was done.
Are Any Other ADs Affected By This Action? (ii) Replace any horizontal stabilizer attachment
fitting if you find any cracks, fretting, or
(b) Yes. This AD supersedes AD 98-10-12; Amendment 39-10524. corrosion.
(3) For all airplanes: Repetitively replace the Every 850 hours TISFollow Revo, Inc.
What Airplanes Are Affected by This AD? horizontal stabilizer attachment fittings upon Service Bulletin B–78,
accumulating 850 hours TIS on the fittings. dated April 3, 1998,
(c) This AD affects Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA- paragraphs 2 and 3 of
4-200, all serial numbers, that are certificated in any category. the INSPECTION and
REPAIR section and
What is the Unsafe Condition Presented in This AD? the APPENDIX.
(4) For all airplanes: Measure the gap between Before further flight after Follow Revo, Inc.
(d) This AD is the result of several reports of fatigue cracks found in the horizontal stabilizer the horizontal skin and the horizontal stabilizer any replacement of the Service Bulletin B–78,
attachment fitting (part number (P/N) 2-2200-21) of Model LA-4-200 airplanes and one report of a attachment fitting (P/N 2–2200–21). If gap is fitting required by dated April 3, 1998.
Model LA-4-200 airplane accident with a fatality attributed to a fatigue crack in the horizontal less than 1⁄16-inch, trim the skin to provide at paragraphs (e)(1), (e)(2),
stabilizer attachment fitting. We are issuing this AD to detect, correct, and prevent future cracks in least 1⁄16-inch gap. and (e)(3) of this AD.
the horizontal stabilizer attachment fitting (P/N 2-2200-21), which could result in failure of the
horizontal stabilizer attachment fitting. This failure could result in loss of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
5 6
(5) For all airplanes: Repetitively inspect (visual) Repetitively inspect at Follow the procedures
the horizontal stabilizer attachedment fitting whichever of the presented in the
using the following procedures. following that occurs first Actions column of this
(i) Move the elevator as required to see the fitting, (first repetitive starts paragraph, including
ensuring that the aft face of the fitting is after the initial inspection the sketch on page 1 of
visible. or replacement): the Service Bulletin B–
(ii) Clean the fitting. Pay special attention to the • 50 hours TIS; or 78.
radius edges of the fitting just outboard of the • the next annual
fitting ear. inspection Replace the
(iii) Visually inspect the fitting for cracks using a fitting prior to further
flashlight (a small magnifying glass or flight after any
borescope is recommended). Pay special inspection where cracks
attention again to the radius edges just outboard are found.
of the fitting ear. Also, inspect as far forward
on the edge that is possible because some
cracks progress along the forward face of the
fitting that is mostly hidden by the horizontal
stabilizer rear beam.
(iv) Reference the sketch on page 1 of the Service
Bulletin B–78 to see where the crack is likely
to begin.
(v) Replace the fitting prior to further flight if
cracks are found during any of these
inspections.
(6) For all airplanes: Report to FAA the results Within 10 days after the Send the form (Figure
of the initial inspection required by paragraph inspection required by 1 of this AD) to FAA,
(e)(2) of this AD even if no damage is found, paragraph (e)(2) or (e)(5) Atlanta ACO, 1895
and report the results of the repetitive of this AD or within 10 Phoenix Boulevard,
inspections required by paragraph (e)(2) of this days after July 8, 2005 suite 450, Atlanta,
AD only if cracks are found. The Office of (the effective date of this Georgia 30349;
Management and Budget (OMB) approved the AD), whichever occurs telephone: (770) 703–
information collection requirements contained later. 6078; facsimile: (770)
in this regulation under the provisions of 703–6097.
Paperwork Reduction Act of 1980 (44 U.S.C.
3501 and those following sections) and
May I Request an Alternative Method of Compliance?
assigned OMB Control Number 2120–0056.
(7) For all airplanes: Do not install used As of July 8, 2005 (the Not Applicable. (f) You may request a different method of compliance or a different compliance time for this AD
serviceable fittings, unless you know the effective date of this by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
number of accumulated hours TIS and have AD). your principal inspector. The principal inspector may add comments and will send your request to the
inspected following the requirements of Manager, Atlanta Aircraft Certification Office (ACO), FAA. For information on any already
paragraph (e)(2) of this AD. approved alternative methods of compliance, contact Cindy Lorenzen, Aerospace Engineer, FAA,
Atlanta ACO, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone: (770) 703-
6078; facsimile: (770) 703-6097.
May I Obtain a Special Flight Permit for the Initial Inspection or Replacement Requirement of
This AD?
(g) Yes. Special flight permits are allowed for this AD with these limitations:
(1) Vne reduced to 121 m.p.h. (105 knots); and
(2) No flight into known turbulence.
7 8
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the instructions in Revo, Inc. Service
Bulletin B-78, dated April 3, 1998. The Director of the Federal Register approved the incorporation EASA EMERGENCY AIRWORTHINESS DIRECTIVE
by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a
copy of this service information, contact Revo, Incorporated, 1396 Grandview Boulevard, AD N° : 2005-0017
Kissimmee, FL 34744. To review copies of this service information, go to the National Archives and
Records Administration (NARA). For information on the availability of this material at NARA, go Issued/Date: 20 April 2005
to: http://www.archives.gov /federal_register/code_of_federal_regulations/ibr_locations.html or call Cancelled: 8 July 2005
(202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, S.W., Nassif Building, Room PL-401, Washington, DC 20590-
001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2005-21092;
Directorate Identifier 2005-CE-20-AD. 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.
Issued in Kansas City, Missouri, on June 2, 2005.
Kim Smith,
Acting Manager, Small Airplane Directorate, Aircraft Certification Service. Type Approval Holder’s Name Type/Model designation(s)
[FR Doc. 05-11361 Filed 6-9-05; 8:45 am]
BILLING CODE 4910-13-P REVO, INCORPORATED Colonial C-2
Lake LA-4
Lake LA-4A
Lake LA-4P
Lake LA-4-200
TCDS Number: FAA 1A13 Rev 26
Foreign AD Nr: FAA AD98-10-12
Supersedure: This Emergency AD has been superseded by FAA AD 2005-12-02.
ATA 300 - EMPENNAGE - INSPECTION
Manufacturer: Lake/Global Amphibians LLC/Revo, Inc
Applicability: Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P,
Lake LA-4-200
Reason: A fatal accident in Finland has been investigated and it has
been determined that cause of the accident was failure of
the rear fitting of the left horizontal stabilizer attachment
fitting (P/N 2-2200-21). FAA AD 98-10-12 required
inspection of these fittings in accordance with REVO Service
Bulletin B-78; this aircraft had complied with the FAA AD.
Subsequent inspection of horizontal stabilizer attachment
fittings has revealed that cracking can occur even if there is
no fretting or interference. As the cracking can occur on the
hidden side of the fitting, this Emergency AD has been
9
revised to require removal and inspection of the fitting
regardless of the gap between the horizontal stabiliser rear Ref. Publications: REVO Service Bulletin B-78 which may be obtained from the
beam and the attachment fitting. Type Certificate holder
Furthermore a replacement time is introduced, beyond Revo Inc
which point the inspection requirement alone is considered 1396 Grandview Boulevard
inadequate to prevent an unsafe condition developing prior Kissimmee
to any further necessary action being established by the Florida 34744
manufacturer. USA
EASA Approval number 2005-3710 dated 20 April 2005 Remarks This Emergency AD has been superseded by FAA action.
and date
Any queries regarding this Emergency AD should be
Effective Date: 20 April 2005 directed to : roger.hardy@easa.eu.int
Compliance: Perform the following actions within 25 hours time in service:
A. If horizontal stabilizer attachment fitting (P/N 2-2200-21)
has more than 1500 hours total time in service, replacement
of the fitting is required.
B. If horizontal stabilizer attachment fitting (P/N 2-2200-21)
has less than 1500 hours total time in service, remove it and
inspect using dye penetrant methods in accordance with the
INSPECTION AND REPAIR section of the REVO Service
Bulletin B-78. If any cracks, fretting or corrosion is present
in the fitting, replace it before further flight in accordance
with the INSPECTION AND REPAIR section of the REVO
Service Bulletin B-78. This action is not necessary if the
fitting has already been removed and inspected in
accordance with the initial issue of this Airworthiness
Directive.
C. Measure the gap between the horizontal stabilizer skin
and the attachment fitting in accordance with the
PROCEDURE section in REVO Service Bulletin B-78.
1. If the clearance is less than 1.6 mm (1/16 in) but the
clearance measured under paragraph A is more than 4.0
mm (5/32 in), prior to further flight, trim the skin in
accordance with the PROCEDURE section in REVO
Service Bulletin B-78 to provide at least 1.6 mm clearance.
D. Inform the EASA Certification Manager General Aviation
about the results of the inspections performed in accordance
with this Directive.
The actions required in this Airworthiness Directive may only
be performed by an approved maintenance organisation in
accordance with its scope of approval.
Lufttüchtigkeitsanweisung [Federal Register: May 6, 2005 (Volume 70, Number 87)]
LTA-Nr.: D-2001-135R4 [Rules and Regulations]
ersetzt: D-2001-135R3 [Page 23930-23934]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 20.07.2005 [DOCID:fr06my05-3]
Muster: Kelly Aerospace AD der ausländischen Behörde: –––––––––––––––––––––––––––––––––––-
B-Series Combustion Heaters FAA AD 2004-25-16R1 Amdt. 39-14076
Geräte-Nr.: Technische Mitteilungen des Herstellers: DEPARTMENT OF TRANSPORTATION
-keine- Kelly Aerospace Power Systems Service Bulletin No. A-107A vom
06.09.2002 Federal Aviation Administration
Piper Vendor Service Publication VSP-150 vom 31.01.2003
14 CFR Part 39
Betroffenes Luftfahrtgerät:
Kelly Aerospace [Docket No. FAA-2004-19693; Directorate Identifier 2004-CE-40-AD; Amendment 39-14076;
B-Series Combustion Heaters AD 2004-25-16 R1]
- Baureihen: B1500, B2030, B2500, B3040, B3500, B4050 und B4500 B-Serie RIN 2120-AA64
Hinweis:
Kabinenheizgeräte dieser Baureihen wurden auch durch die Firmen ElectroSystems, Airworthiness Directives; Kelly Aerospace Power Systems Part Number (P/N) 14D11, A14D11,
JanAero Devices, Janitrol, C&D Airmotive Products, FL Aerospace und Midland-Ross B14D11, C14D11, 23D04, A23D04, B23D04, C23D04, or P23D04 Fuel Regulator Shutoff Valves
Corporation hergestellt. (Formerly Owned by ElectroSystems, JanAero Devices, Janitrol, C&D Airmotive Products, FL
Aerospace, and Midland-Ross Corporation)
- Werk-Nrn.: Alle, ausgerüstet mit Kraftstoffabschaltventilen mit den Kelly Aerospace-Teilenummern
(P/N's) 14D11, A14D11, B14D11, C14D11, 23D04, A23D04, B23D04, C23D04 oder
P23D04 AGENCY: Federal Aviation Administration (FAA), DOT.
Betrifft: ACTION: Final rule.
Kabinenheizgerät, Kraftstoffregler und Kraftstoffabschaltventil (combustion heater, fuel regulator, shutoff
valve, ATA-Code 21-40-00) - Kraftstoffleckagen am Kabinenheizgerät durch Undichtigkeiten am Kraftstoff- –––––––––––––––––––––––––––––––––––-
regler und am Kraftstoffabschaltventil - ggf. kann dieser Fehler zur Entstehung von Bränden im Fluge SUMMARY: The FAA is revising Airworthiness Directive (AD) 2004-25-16, which applies to
führen.
aircraft equipped with a fuel regulator shutoff valve part number (P/N) 14D11, A14D11, B14D11,
Maßnahmen: C14D11, 23D04, A23D04, B23D04, C23D04, or P23D04 used with B1500, B2030, B2500, B3040,
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA B3500, B4050, or B4500 B-Series combustion heaters. AD 2004-25-16 currently requires you to
Airworthiness Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen. repetitively inspect the fuel regulator shutoff valve (visually or by pressure test) for fuel leakage and
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, replace the fuel regulator shutoff valve with an improved design replacement part with a
vollständig und innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchge- manufacturer's date code of 02/02 or later if fuel leakage is found. AD 2004-25-16 also allows you to
führt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung
bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
disable the heater as an alternative method of compliance. Since we issued AD 2004-25-16, we
received several comments requesting a revision to paragraph (e)(2). Consequently, this AD retains
Fristen: the actions required in AD 2004-25-16 and revises the requirements in paragraph (e)(2) to remove a
Alle anzuwendenden Fristen sind der oben genannten FAA Airworthiness Directive zu entnehmen. required action. We are issuing this AD to prevent failure of the fuel regulator shutoff valve, which
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten could result in fuel leakage in aircraft with these combustion heaters. This failure could result in an
FAA Airworthiness Directive. aircraft fire.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2004-25-16R1 Amdt. 39-14076 DATES: This AD becomes effective on June 20, 2005.
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen On January 5, 2005 (69 FR 75228, December 16, 2004), the Director of the Federal Register
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 approved the incorporation by reference of Kelly Aerospace Power Systems Service Bulletin No. A-
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen. 107A, Issue Date: September 6, 2002; and Piper Vendor Service Publication VSP-150, dated January
Rechtsbehelfsbelehrung: 31, 2003.
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.
ADDRESSES: To get the service information identified in this AD, contact Kelly Aerospace Power
LTAs werden auch im Internet unter http://www.lba.de publiziert Systems, P.O. Box 273, Fort Deposit, Alabama 36032; telephone: (334) 227-8306; facsimile: (334)
***
227-8596; Internet: http://www.kellyaerospace.com.
1
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