Nachrichten für Luftfahrer 2008 Teil II (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung [Federal Register: July 29, 2008 (Volume 73, Number 146)]
LTA-Nr.: D-2008-281 [Rules and Regulations]
[Page 43845-43847]
Luftfahrt-Bundesamt From the Federal Register Online via GPO Access [wais.access.gpo.gov]
Datum der Bekanntgabe: 12.08.2008 [DOCID:fr29jy08-1]
Muster: Cessna AD der ausländischen Behörde:
Cessna 175 FAA AD 2008-15-06 Amdt. 39-15618 ––––––––––––––––––––––––––––––––––
Geräte-Nr.: Technische Mitteilungen des Herstellers:
596 Cessna Single Engine Service Bulletin SEB07-2 Revision 2 vom DEPARTMENT OF TRANSPORTATION
18.06.2007
Federal Aviation Administration
Betroffenes Luftfahrtgerät:
14 CFR Part 39
Cessna
Cessna 175
[Docket No. FAA-2007-29240; Directorate Identifier 2007-CE-076-AD; Amendment 39-15618;
- Baureihen: 175, 175A AD 2008-15-06]
- Werk-Nrn.: Cessna 175: RIN 2120-AA64
626, 640, 28700A und 55001 bis 56238
Cessna 175A:
Airworthiness Directives; Cessna Aircraft Company Models 175 and 175A Airplanes
691 und 56239 bis 56777
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
Betrifft:
Möglicher Verlust des Triebwerks im Fluge durch Bruch der Motoraufhängung am Brandschott. ACTION: Final rule.
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, SUMMARY: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente Company (Cessna) Models 175 and 175A airplanes. This AD requires you to check the airplane
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits- logbook to determine if the original engine mounting brackets have been replaced. If the original
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt. engine mounting brackets are still installed, this AD requires you to repetitively inspect those
brackets for cracks and replace any cracked engine mounting bracket. After replacing all four original
Fristen: engine mounting brackets, no further action will be required by this AD. This AD was prompted by a
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 report that the engine became detached from the firewall during landing on one of the affected
FAA Airworthiness Directive. airplanes. We are issuing this AD to detect and correct cracks in the engine mounting brackets, which
could result in failure of the engine mounting bracket. This failure could lead to the engine detaching
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der from the firewall.
FAA AD 2008-15-06 Amdt. 39-15618
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 DATES: This AD becomes effective on September 2, 2008.
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.
On September 2, 2008, the Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD.
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. ADDRESSES: For service information identified in this AD, contact Cessna Aircraft Company,
LTAs werden auch im Internet unter http://www.lba.de publiziert
Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-
*** 9006.
To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC
20590, or on the Internet at http://www.regulations.gov. The docket number is FAA-2007-29240;
Directorate Identifier 2007-CE-076-AD.
1
Aktenzeichen: (01)T23-502.1/D-2008-281 Seite 1 von 1
FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, 1801 Airport Authority for This Rulemaking
Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-4107.
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
SUPPLEMENTARY INFORMATION: 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.
Discussion 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
On March 31, 2008, we issued a proposal to amend part 39 of the Federal Aviation Regulations promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
(14 CFR part 39) to include an AD that would apply to certain Cessna Models 175 and 175A methods, and procedures the Administrator finds necessary for safety in air commerce. This
airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking regulation is within the scope of that authority because it addresses an unsafe condition that is likely
(NPRM) on April 8, 2008 (73 FR 19017). The NPRM proposed to require you to check the airplane to exist or develop on products identified in this AD.
logbook to determine if the original engine mounting brackets have been replaced. If the original
engine mounting brackets are still installed, the NPRM proposed to require you to repetitively inspect Regulatory Findings
those brackets for cracks and replace any cracked engine mounting bracket. After replacing all four
original engine mounting brackets, no further action would be required by the NPRM. 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
Comments national government and the States, or on the distribution of power and responsibilities among the
various levels of government.
We provided the public the opportunity to participate in developing this AD. We received no For the reasons discussed above, I certify that this AD:
comments on the proposal or on the determination of the cost to the public. 1. Is not a ''significant regulatory action'' under Executive Order 12866;
2. Is not a ''significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034,
Conclusion February 26, 1979); and
3. Will not have a significant economic impact, positive or negative, on a substantial number of
We have carefully reviewed the available data and determined that air safety and the public small entities under the criteria of the Regulatory Flexibility Act.
interest require adopting the AD as proposed except for minor editorial corrections. We have We prepared a summary of the costs to comply with this AD (and other information as included
determined that these minor corrections: in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary
• Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; by sending a request to us at the address listed under ADDRESSES. Include ''Docket No. FAA-2007-
and 29240; Directorate Identifier 2007-CE-076-AD'' in your request.
• Do not add any additional burden upon the public than was already proposed in the NPRM.
List of Subjects in 14 CFR Part 39
Costs of Compliance
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
We estimate that this AD affects 1,218 airplanes in the U.S. registry.
We estimate the following costs to do the inspection: Adoption of the Amendment
Labor Cost Parts Cost Total Cost Total Cost on U.S. Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation
Per Airplane Operators Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
7.5 work-hours X $80 per Not applicable $600 $730,800 PART 39–AIRWORTHINESS DIRECTIVES
hour = $600
1. The authority citation for part 39 continues to read as follows:
We estimate the following costs to do any necessary replacements:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Labor Cost Parts Cost Total Cost Per Airplane
§ 39.13 [Amended]
3 work-hours per bracket X $80 per hour $200 per bracket. 4 X $440 per bracket. $1,760 to
= $240 per bracket. 4 brackets per $200 = $800 for all 4 replace all 4 brackets. 2. FAA amends § 39.13 by adding the following new AD:
airplane X $240 per bracket = $960. brackets.
2 3
AIRWORTHINESS DIRECTIVE (2) If you can positively Not applicable. Make an entry into the
FAA determine that all four of the aircraft logbook showing
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/ original engine mounting compliance with this portion
www.gpoaccess.gov/fr/advanced.html brackets have been replaced, no of the AD in accordance with
further action is required. 14 CFR 43.9. The
2008-15-06 Cessna Aircraft Company: Amendment 39-15618; Docket No. FAA-2007-29240; owner/operator holding at
Directorate Identifier 2007-CE-076-AD. least a private pilot certificate
as authorized by section 43.7
Effective Date may do this action.
(3) If you cannot positively Initially inspect within the next Follow Cessna Single Engine
(a) This AD becomes effective on September 2, 2008.
determine that all four of the 12 months after September 2, Service Bulletin SEB07-2,
original engine mounting 2008 (the effective date of this Revision 2, dated June 18,
Affected ADs brackets have been replaced, AD). If no cracks are found, 2007.
inspect each of the upper and repetitively inspect thereafter at
(b) None.
lower engine mounting brackets intervals not to exceed 500
on both the left and right sides hours time-in-service (TIS) until
Applicability for cracks as specified in the all four of the original engine
service bulletin. mounting brackets are replaced.
(c) This AD applies to the following airplane models and serial numbers that are certificated in
any category: (4) If cracks are found in any of Before further flight after the Follow Cessna Single Engine
the engine mounting brackets inspection in which cracks are Service Bulletin SEB07-2,
Model Serial Nos. Year manufactured during any inspection required found. Replacing the cracked Revision 2, dated June 18,
in paragraph (e)(3) of this AD, engine mounting bracket 2007.
(1) 175 55001 through 55703 1958. replace the cracked engine terminates the repetitive
mounting bracket(s). inspection required in paragraph
(2) 175 55704 through 56238 1959.
(e)(3) of this AD only for the
(3) 175 28700A, 626, and 640 1958 and 1959. replaced engine mounting
(4) 175A 691, and 56239 through 56777 1960. bracket.
(5) To terminate the repetitive At any time before or after the Follow Cessna Single Engine
Unsafe Condition inspections required in initial inspection required in Service Bulletin SEB07-2,
paragraph (e)(3) of this AD, you paragraph (e)(3) of this AD. Revision 2, dated June 18,
(d) A report that the engine became unattached from the firewall during landing on one of the may replace all four original 2007.
affected airplanes prompts this AD. We are issuing this AD to detect and correct cracks in the engine engine mounting brackets.
mounting brackets, which could result in failure of the engine mounting bracket. This failure could (6) Dispose of every replaced Before further flight after the Not applicable.
lead to the engine detaching from the firewall. bracket following 14 CFR engine mounting bracket is
43.10, paragraph (c)(6), which removed for replacement.
Compliance states the following:
“Mutilation. The part may be
(e) To address this problem, you must do the following, unless already done: mutilated to deter its installation
in a type certificated product.
Actions Compliance Procedures The mutilation must render the
part beyond repair and
(1) Check the airplane logbook Within the next 30 days after The owner/operator holding incapable of being reworked to
to determine if all four of the September 2, 2008 (the effective at least a private pilot appear to be airworthy.”
original engine mounting date of this AD). certificate as authorized by
brackets have been replaced. section 43.7 may do this
action. Alternative Methods of Compliance (AMOCs)
(f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to
ATTN: Gary Park, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100,
4 5
Wichita, Kansas 67209; telephone: 316-946-4123; fax: 316-946-4107; e-mail address: Lufttüchtigkeitsanweisung
gary.park@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, LTA-Nr.: D-2008-282
notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO. Luftfahrt-Bundesamt
Datum der Bekanntgabe: 12.08.2008
Material Incorporated by Reference Muster: General Electric AD der ausländischen Behörde:
CF34 FAA AD 2008-16-01 Amdt. 39-15619
(g) You must use Cessna Single Engine Service Bulletin SEB07-2, Revision 2, dated June 18, Geräte-Nr.: Technische Mitteilungen des Herstellers:
2007, to do the actions required by this AD, unless the AD specifies otherwise. 6341 General Electric Alert Service Bulletin CF34-8E-AL S/B 73-A0019
(1) The Director of the Federal Register approved the incorporation by reference of this service vom 17.06.2008
information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact Cessna Aircraft Company, Product Betroffenes Luftfahrtgerät:
Support, P.O. Box 7706, Wichita, Kansas 67277.
(3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 General Electric
CF34
Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: - Baureihen: CF34-8E Serie
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
- Werk-Nrn.: Alle Triebwerke dieser Serie mit FADEC-Systemen mit den Hersteller-Teilenummern
Issued in Kansas City, Missouri, on July 15, 2008. (P/N's) 4120T00P47, 4120T00P48, 111E9320G48 oder 111E9320G49.
Kim Smith,
Betrifft:
Manager, Small Airplane Directorate, Aircraft Certification Service. Möglicher Verlust der Schubregelung im Fluge durch einen Softwarefehler im FADEC-System.
[FR Doc. E8-16583 Filed 7-28-08; 8:45 am]
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 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.
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 2008-16-01 Amdt. 39-15619
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
***
6
Aktenzeichen: (10)T23-502.1/D-2008-282 Seite 1 von 1
[Federal Register: July 31, 2008 (Volume 73, Number 148)] FOR FURTHER INFORMATION CONTACT: Kenneth Steeves, Aerospace Engineer, Engine
[Rules and Regulations] Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park,
[Page 44628-44630] Burlington, MA 01803; e-mail: kenneth.steeves@faa.gov; telephone (781) 238-7765; fax (781) 238-
From the Federal Register Online via GPO Access [wais.access.gpo.gov] 7199.
[DOCID:fr31jy08-5]
SUPPLEMENTARY INFORMATION: We have received reports of six events on CF34-8E
–––––––––––––––––––––––––––––––––– turbofan engines that resulted in loss of thrust control. On March 2, 2008, the No. 1 engine on an ERJ
170 experienced a fluctuation of the interstage turbine temperature during decent that resulted in
DEPARTMENT OF TRANSPORTATION changes in thrust. The crew shut down the engine. On May 12, 2008, an ERJ 170 was at cruise when
the ENG 2 Control Fault posted to the Engine Indicating and Crew Alerting System (EICAS) display.
Federal Aviation Administration The FADEC software commanded the number two engine to idle and there was no response to
throttle movement by the crew. The crew shut down the engine. Four more similar events occurred
14 CFR Part 39 on May 29, June 10, June 14, and July 10, 2008, all resulting in loss of thrust control with an ENG 1
or 2 Control Fault message posted to the EICAS. Our investigation revealed that all events resulted
[Docket No. FAA-2008-0821; Directorate Identifier 2008-NE-20-AD; Amendment 39-15619; from the same software fault scenario. We attribute the fault to FADEC software version 8Ev5.40.
AD 2008-16-01] This condition, if not corrected, could result in loss of thrust control and controllability of the
airplane.
RIN 2120-AA64
FAA's Determination and Requirements of This AD
Airworthiness Directives; General Electric Co. (GE) CF34-8E Series Turbofan Engines
The unsafe condition described previously is likely to exist or develop on other GE CF34-8E
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). series turbofan engines of the same type design. For that reason, we are issuing this AD to prevent
loss of thrust control and controllability of the airplane.
ACTION: Final rule; request for comments.
FAA's Determination of the Effective Date
––––––––––––––––––––––––––––––––––
Since an unsafe condition exists that requires the immediate adoption of this AD, we have found
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE CF34-8E series that notice and opportunity for public comment before issuing this AD are impracticable, and that
turbofan engines with certain part number (P/N) full authority digital engine controls (FADECs) good cause exists for making this amendment effective in less than 30 days.
installed. This AD requires reprogramming the FADEC software from version 8Ev5.40 to an FAA-
approved software version. This AD results from six loss of thrust control events from the same Comments Invited
software fault scenario. We are issuing this AD to prevent loss of thrust control and controllability of
the airplane. This AD is a final rule that involves requirements affecting flight safety and was not preceded by
notice and an opportunity for public comment; however, we invite you to send us any written relevant
DATES: This AD becomes effective August 15, 2008. data, views, or arguments regarding this AD. Send your comments to an address listed under
We must receive any comments on this AD by September 29, 2008. ADDRESSES. Include ''AD Docket No. FAA-2008-0821; Directorate Identifier 2008-NE-20-AD'' in
the subject line of your comments. We specifically invite comments on the overall regulatory,
ADDRESSES: Use one of the following addresses to comment on this AD: economic, environmental, and energy aspects of the rule that might suggest a need to modify it.
• Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for We will post all comments we receive, without change, to http://www.regulations.gov, including
sending your comments electronically. any personal information you provide. We will also post a report summarizing each substantive
• Mail: U.S. Docket Management Facility, Department of Transportation, 1200 New Jersey verbal contact with FAA personnel concerning this AD. Using the search function of the Web site,
Avenue, SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001. anyone can find and read the comments in any of our dockets, including, if provided, the name of the
• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through individual who sent the comment (or signed the comment on behalf of an association, business, labor
Friday, except Federal holidays. union, etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register
• Fax: (202) 493-2251. published on April 11, 2000 (65 FR 19477-78).
Contact General Electric Company via Lockheed Martin Technology Services, 10525 Chester
Road, Suite C, Cincinnati, Ohio 45215; telephone (513) 672-8400; fax (513) 672-8422, for the Examining the AD Docket
service information identified in this AD.
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at
the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Operations office (telephone (800) 647-5527) is
1 2
the same as the Mail address provided in the ADDRESSES section. Comments will be available in AIRWORTHINESS DIRECTIVE
the AD docket shortly after receipt. FAA
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/
Authority for This Rulemaking www.gpoaccess.gov/fr/advanced.html
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. 2008-16-01 General Electric Co.: Amendment 39-15619. Docket No. FAA-2008-0821; Directorate
Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Identifier 2008-NE-20-AD.
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, Effective Date
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, (a) This airworthiness directive (AD) becomes effective August 15, 2008.
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 Affected ADs
to exist or develop on products identified in this rulemaking action.
(b) None.
Regulatory Findings
Applicability
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 (c) This AD applies to General Electric Co. (GE) CF34-8E series turbofan engines with full
national Government and the States, or on the distribution of power and responsibilities among the authority digital electronic controls (FADECs), part numbers (P/N) 4120T00P47, 4120T00P48,
various levels of government. 111E9320G48, or 111E9320G49, installed. These engines are installed on, but not limited to,
For the reasons discussed above, I certify that this AD: Empresa Brasileira de Aeronautica S.A. (EMBRAER) ERJ 170 series airplanes.
1. Is not a ''significant regulatory action'' under Executive Order 12866;
2. Is not a ''significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, Unsafe Condition
February 26, 1979); and
3. Will not have a significant economic impact, positive or negative, on a substantial number of (d) This AD results from six loss of thrust control events from the same software fault scenario.
small entities under the criteria of the Regulatory Flexibility Act. We are issuing this AD to prevent loss of thrust control and controllability of the airplane.
We prepared a summary of the costs to comply with this AD and placed it in the AD Docket.
You may get a copy of this summary at the address listed under ADDRESSES. Compliance
List of Subjects in 14 CFR Part 39 (e) You are responsible for having the actions required by this AD performed within 660 flight
hours time-in-service after the effective date of this AD, unless the actions have already been done.
Air transportation, Aircraft, Aviation safety, Safety.
Removal of CF34-8E FADEC Software Version 8Ev5.40
Adoption of the Amendment
(f) For CF34-8E engines with a FADEC, P/N 4120T00P47, 4120T00P48, 111E9320G48, or
Under the authority delegated to me by the Administrator, the Federal Aviation Administration 111E9320G49, installed, do either of the following:
amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: (1) Replace the FADEC, P/N 4120T00P47, 4120T00P48, 111E9320G48, or 111E9320G49, with
a FADEC P/N not listed in paragraph (c) of this AD. Or,
PART 39–AIRWORTHINESS DIRECTIVES (2) For CF34-8E engines with a FADEC, P/N 4120T00P47, 4120T00P48, 111E9320G48, or
111E9320G49, installed, reprogram the FADEC software to an FAA approved version.
1. The authority citation for part 39 continues to read as follows:
Installation Prohibition
Authority: 49 U.S.C. 106(g), 40113, 44701.
(g) After the effective date of this AD, don't install any FADEC, P/N 4120T00P47, 4120T00P48,
§ 39.13 [Amended] 111E9320G48, or 111E9320G49, onto any CF34-8E engine.
2. The FAA amends § 39.13 by adding the following new airworthiness directive:
3 4
Alternative Methods of Compliance Lufttüchtigkeitsanweisung
LTA-Nr.: D-2008-283
(h) The Manager, Engine Certification Office, has the authority to approve alternative methods
of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Luftfahrt-Bundesamt
Datum der Bekanntgabe: 12.08.2008
Related Information Muster: MD Helicopters AD der ausländischen Behörde:
Hughes 369 FAA AD 2008-15-03 Amdt. 39-15615
(i) General Electric Alert Service Bulletin CF34-8E-AL S/B 73-A0019, dated June 17, 2008, Geräte-Nr.: Technische Mitteilungen des Herstellers:
contains information on removing software version 8Ev5.40 and installing an FAA-approved 3036 1. Helicopter Technology Company Mandatory Service Bulletin
FADEC software version. Notice Nr. 3100-4R4 vom 10.05.2006
2. MD Helicopters Service Bulletin 369D-203R1 vom 23.01.2006
(j) Contact Kenneth Steeves, Aerospace Engineer, Engine Certification Office, FAA, Engine & 3. MD Helicopters Service Bulletin 369E-097R1 vom 23.01.2006
4. MD Helicopters Service Bulletin 369F-082R1 vom 23.01.2006
Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: 5. MD Helicopters Service Bulletin 369H-246R1 vom 23.01.2006
kenneth.steeves@faa.gov; telephone (781) 238-7765; fax (781) 238-7199, for more information
about this AD. Betroffenes Luftfahrtgerät:
Material Incorporated by Reference MD Helicopters
Hughes 369
(k) None.
- Baureihen: 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS
OH-6A
Issued in Burlington, Massachusetts, on July 23, 2008.
Carlos Pestana, - Werk-Nrn.: Alle Helikopter dieser Baureihen mit folgenden Heckrotorblättern:
Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. E8-17422 Filed 7-30-08; 8:45 am] Helicopter Technology Company, LLC Teilenummern (P/N's):
500P3100-101 und -103
500P3100-301 und -303
500P3300-501 und -503
500P3500-701 und -703
MD Helicopters, Inc. Teilenummern (P/N's):
369D21640-501, -503 und -505
369D21641-501, -503 und -505
369D21643-501, -503 und -505
369D21642-501, -503 und -505
einschließlich aller Heckrotorblätter mit den Farbmarkierungen ''M'' oder ''I'' an der
Blattwurzel.
Betrifft:
Mögliche Vibrationen am Heckrotor und Bruch von Heckrotorblättern infolge von Unwucht nach dem
Verlust von Erosionsschutzkanten.
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA
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 Lufttüchtigkeits-
anweisung 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 2008-15-03 Amdt. 39-15615
5
Aktenzeichen: (02)T23-502.1/D-2008-283 Seite 1 von 2
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 [Federal Register: July 30, 2008 (Volume 73, Number 147)]
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es [Rules and Regulations]
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
[Page 44139-44140]
Rechtsbehelfsbelehrung: From the Federal Register Online via GPO Access [wais.access.gpo.gov]
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. [DOCID:fr30jy08-3]
LTAs werden auch im Internet unter http://www.lba.de publiziert
*** ––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0287; Directorate Identifier 2006-SW-15-AD; Amendment 39-15615;
AD 2008-15-03]
RIN 2120-AA64
Airworthiness Directives; MD Helicopters, Inc. Model 369A, OH-6A, 369D, 369E, 369F, 369FF,
369H, 369HE, 369HM, and 369HS Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc.
(MDHI) Model 369A, OH-6A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, and 369HS
helicopters that requires repetitive tap inspections of each tail rotor (T/R) blade abrasion strip. This
amendment is prompted by an incident in which an abrasion strip separated from a T/R blade. The
actions specified by this AD are intended to prevent disbonding and subsequent separation of an
abrasion strip from a T/R blade, which could result in vibration, loss of the T/R, and subsequent loss
of control of the helicopter.
DATES: Effective September 3, 2008.
The incorporation by reference of certain publications listed in the regulations is approved by the
Director of the Federal Register as of September 3, 2008.
ADDRESSES: You may get the Helicopter Technology Company, LLC (HTC) service information
identified in this AD from HTC, 12902 South Broadway, Los Angeles, California, 90061, telephone
(310) 523-2750, fax (310) 523-2745, or on the Internet at http://www.helicoptertech.com. The service
information referenced in Note 2 of this AD may be obtained from MD Helicopters Inc., Attn:
Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215-9734,
telephone (800) 388-3378, fax (480) 346-6813, or on the Internet at http://www.mdhelicopters.com.
Examining the Docket: You may examine the docket that contains this AD, any comments, and
other information on the Internet at http://www.regulations.gov or at the Docket Operations office,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
1
Aktenzeichen: (02)T23-502.1/D-2008-283 Seite 2 von 2
FOR FURTHER INFORMATION CONTACT: John Cecil, Aviation Safety Engineer, FAA, Los 2. Is not a ''significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034,
Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, February 26, 1979); and
California 90712-4137, telephone (562) 627-5228, fax (562) 627-5210. 3. Will not have a significant economic impact, positive or negative, on a substantial number of
small entities under the criteria of the Regulatory Flexibility Act.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to include an AD for We prepared an economic evaluation of the estimated costs to comply with this AD. See the AD
the specified model helicopters was published in the Federal Register on March 13, 2008 (73 FR docket to examine the economic evaluation.
13515). That action proposed to require, within 25 hours time-in-service (TIS), and thereafter at
intervals not to exceed 25 hours TIS, tap inspections of the upper and lower surfaces of each T/R Authority for This Rulemaking
blade abrasion strip using a coin (United States 25-cent piece or equivalent), or a small brass, mild
steel, or aluminum hammer, to detect bonding voids that exceed 0.2 square inch in size with a Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
minimum of 1.0 inch between voids, at least 75 percent of the bonded area of the abrasion strip being Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
free from voids, and no voids at the edge of the abrasion strip. Also proposed was a terminating Programs, describes in more detail the scope of the Agency's authority.
action of modifying each T/R blade in accordance with FAA-approved data by installing a titanium We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III,
rivet in the tip of the outboard end of each T/R blade and painting a ''T'' on the root-end of the T/R section 44701, ''General requirements.'' Under that section, Congress charges the FAA with
blade. promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
We have reviewed the following service information: methods, and procedures the Administrator finds necessary for safety in air commerce. This
• HTC Mandatory Service Bulletin Notice No. 3100-4R4, dated May 10, 2006, which describes regulation is within the scope of that authority because it addresses an unsafe condition that is likely
procedures for periodic inspection of the abrasion strip-to-skin bond integrity on each T/R blade, and to exist or develop on products identified in this rulemaking action.
modifying each T/R blade by installing a titanium rivet, P/N 500P3124-13, in the tip of the T/R
blade, and painting a ''T'' on the root-end of the T/R blade in accordance with applicable engineering List of Subjects in 14 CFR Part 39
drawings or standard repair instructions; and
• MD Helicopters Service Bulletin SB369D-203R1, SB369E-097R1, SB369F-082R1, and Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
SB369H-246R1, dated January 23, 2006, which describes procedures for periodic inspections of the
T/R abrasion strip-to-skin bond integrity and modification of the T/R blade by HTC to install a Adoption of the Amendment
titanium rivet in the tip of the T/R blade.
Interested persons have been afforded an opportunity to participate in the making of this Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation
amendment. No comments were received on the proposal or the FAA's determination of the cost to Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
the public. The FAA has determined that air safety and the public interest require the adoption of the
rule as proposed. PART 39–AIRWORTHINESS DIRECTIVES
The FAA estimates that this AD will affect 718 helicopters of U.S. registry.
• If operators conduct the repetitive inspections required by this AD instead of modifying their T/R 1. The authority citation for part 39 continues to read as follows:
blades by installing a titanium rivet, the estimated costs per year is $229,760 per year, assuming:
• 24 inspections per year per helicopter (600 hours TIS per 25 hour TIS inspection), Authority: 49 U.S.C. 106(g), 40113, 44701.
• Labor of 5 minutes per T/R blade (10 minutes (\1/6\ hour) per helicopter), and
• An average labor rate of $80 per work hour. § 39.13 [Amended]
• If operators elect to implement the terminating action by installing a titanium rivet in each T/R
blade, the estimated total cost is $244,120, assuming: 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows:
• The cost of removing, reinstalling, and balancing the 2-T/R blade set for the entire fleet is
$114,880, assuming that it takes 2 work hours per helicopter to perform these actions at an average
labor rate of $80 per work hour, and
• The cost of installing the rivet in each T/R blade in the fleet is $129,240, which includes the cost
of $10 per rivet ($20 per helicopter), 1 work hour per T/R blade (2 work hours per helicopter) to
install a rivet, at an average labor rate of $80 per work hour.
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
national Government and the States, or on the distribution of power and responsibilities among the
various levels of government.
For the reasons discussed above, I certify that the regulation:
1. Is not a ''significant regulatory action'' under Executive Order 12866;
2 3
AIRWORTHINESS DIRECTIVE (e) The inspection shall be done in accordance with the specified portions of Helicopter
FAA Technology Company, LLC (HTC) Mandatory Service Bulletin Notice No. 3100-4R4, dated May 10,
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/ 2006. The Director of the Federal Register approved this incorporation by reference in accordance
www.gpoaccess.gov/fr/advanced.html with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from HTC, 12902 South Broadway,
Los Angeles, California, 90061, telephone (310) 523-2750, fax (310) 523-2745, or on the Internet at
2008-15-03 MD Helicopters, Inc. (MDHI): Amendment 39-15615. Docket No. FAA-2008-0287; http://www.helicoptertech.com. Copies may be inspected at the FAA, Office of the Regional
Directorate Identifier 2006-SW-15-AD. Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas or at the National
Archives and Records Administration (NARA). For information on the availability of this material at
Applicability: Model 369A, OH-6A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, and NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_
369HS, certificated in any category, with a tail rotor (T/R) blade installed as follows including all regulations/ibr_locations.html.
serial numbers and those T/R blades with an ''M'' or an ''I'' painted on the T/R blade root:
(f) This amendment becomes effective on September 3, 2008.
• Helicopter Technology Company, LLC (HTC) part number (P/N) 500P3100-101 and -103, or
MDHI P/N 369D21640-501, -503, and -505. Issued in Fort Worth, Texas, on June 25, 2008.
• HTC P/N 500P3100-301 and -303, or MDHI P/N 369D21641-501, -503, and -505. David A. Downey,
• HTC P/N 500P3300-501 and -503, or MDHI P/N 369D21643-501, -503, and -505. Manager, Rotorcraft Directorate, Aircraft Certification Service.
• HTC P/N 500P3500-701 and -703, or MDHI P/N 369D21642-501, -503, and -505. [FR Doc. E8-17274 Filed 7-29-08; 8:45 am]
Note 1: An ''M'' or an ''I'' painted on the root of the T/R blade indicates compliance to an
Alternate Method of Compliance (AMOC) to Emergency AD 2003-08-51 (Docket No. 2003-SW-17-
AD, Amendment 39-13215, April 15, 2003), issued by the FAA, Los Angeles Aircraft Certification
Office (LAACO) on June 13, 2003 to HTC. The AMOC addressed shot peening of the pitch horn of
the T/R assembly.
Compliance: Required as indicated.
To prevent disbonding and subsequent separation of an abrasion strip from a T/R blade, which
could result in vibration, loss of the T/R, and subsequent loss of control of the helicopter, accomplish
the following:
(a) Within 25 hours time-in-service (TIS), unless accomplished previously, and thereafter at
intervals not to exceed 25 hours TIS, inspect the abrasion strip-to-skin bond integrity on each T/R
blade using a tap test method in accordance with Part 1–Inspection, in Helicopter Technology
Company, LLC (HTC) Mandatory Service Bulletin Notice No. 3100-4R4, dated May 10, 2006 (SB).
Note 2: MD Helicopters Service Bulletin SB369D-203R1, SB369E-097R1, SB369F-082R1, and
SB369H-246R1, dated January 23, 2006, pertain to the subject of this AD.
(b) Modifying each T/R blade in accordance with FAA-approved data by installing a titanium
rivet at the outboard end and painting the letter ''T'' on the root-end of the T/R blade to indicate the
modification has been accomplished is considered a terminating action for the requirements of this
AD.
(c) To request a different method of compliance or a different compliance time for this AD,
follow the procedures in 14 CFR 39.19. Contact the Manager, Los Angeles Aircraft Certification
Office, FAA, ATTN: John Cecil, Aviation Safety Engineer, 3960 Paramount Blvd., Lakewood,
California 90712-4137, telephone (562) 627-5228, fax (562) 627-5210, for information about
previously approved alternative methods of compliance.
(d) Special flight permits will not be issued.
4 5
