Nachrichten für Luftfahrer 2006 Teil II (weicht ggf. von Druckversion ab)
Regulatory Findings
AIRWORTHINESS DIRECTIVE U.S. Department
of Transportation
We have determined that this AD will not have federalism implications under Executive Order Federal Aviation
www.faa.gov/aircraft/safety/alerts/
13132. This AD will not have a substantial direct effect on the States, on the relationship between the Administration
www.gpoaccess.gov/fr/advanced.html
national government and the States, or on the distribution of power and responsibilities among the
various levels of government.
2006-15-08 Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Engine Division;
For the reasons discussed above, I certify that this AD:
Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona):
(1) Is not a ‘‘significant regulatory action'' under Executive Order 12866;
Amendment 39-14688; Docket No. FAA-2006-23706; Directorate Identifier 2006-NE-03-AD.
(2) Is not a ‘‘significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979); and
Effective Date
(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.
(a) This airworthiness directive (AD) becomes effective August 24, 2006.
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.
Affected ADs
List of Subjects in 14 CFR Part 39
(b) None.
Air transportation, Aircraft, Aviation safety, Safety.
Applicability
Adoption of the Amendment
(c) This AD applies to Honeywell International Inc. TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -
5AB, -5B, -6, -6A, -10, -10AV, -10GP, -10GT, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation
10UGR, -10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR turboprop engines with the part
Administration amends 14 CFR part 39 as follows:
numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies listed in this AD, installed. These
engines are installed on, but not limited to, the following airplanes:
PART 39–AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows: Manufacturer Model
AERO PLANES, LLC (formerly McKinnon Enterprises) G–21G.
Authority: 49 U.S.C. 106(g), 40113, 44701. ALLIED AG CAT PRODUCTIONS (formerly Schweizer) G–164 Series.
AYRES S–2R Series.
§ 39.13 [Amended] BRITISH AEROSPACE LTD (formerly Jetstream) 3101 and 3201 Series, and HP.137
JETSTREAM MK.1.
2. The FAA amends § 39.13 by adding the following new airworthiness directive: CONSTRUCCIONES AERONAUTICAS, S.A. (CASA) C–212 Series.
DEHAVILLAND DH104 Series 7AXC (DOVE).
DORNIER 228 Series.
FAIRCHILD SA226 and SA227 Series
(SWEARINGEN MERLIN and
METRO SERIES).
GRUMMAN AMERICAN G–164 Series.
MITSUBISHI MU–2B Series (MU–2 Series).
PILATUS PC–6 Series (FAIRCHILD PORTER
and PEACEMAKER).
POLSKIE ZAKLADY LOTNICZE SPOLKA (formerly PZL M18, PZL M18A, PZL M18B.
Wytwornia Sprzetu Komunikacyjnego).
PROP-JETS, INC. 400.
RAYTHEON AIRCRAFT (formerly Beech) C45G, TC–45G, C–45H, TC–45H,
TC–45J, G18S, E18S–9700, D18S,
D18C, H18, RC–45J, JRB–6, UC–
45J, 3N, 3NM, 3TM, B100, C90 and
E90.
5 6
Manufacturer Model TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10AV, -10GP, -10GT, -10P, and -10T Series
SHORTS BROTHERS and HARLAND, LTD. SC7 (SKYVAN) Series. Engines
THRUSH (ROCKWELL COMMANDER) S–2R.
TWIN COMMANDER (JETPROP COMMANDER) 680, 690 and 695 Series. (i) For TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10AV, -10GP, -10GT, -10P, and -10T
series engines, replace Woodward FCU assemblies, P/Ns 893561-7/ -8/ -9/ -10/ -11/ -14/ -15/ -16/ -
Unsafe Condition 20/ -26/ -27, and -29, and P/Ns 897770-1/ -3/ -7/ -9/ -10/ -11/ -12/ -14 / -15/ -16/ -25/ -26, and -28,
with a serviceable, modified FCU assembly the next time the FCU assembly is removed for cause
(d) This AD results from reports of loss of the fuel control drive, leading to engine overspeed, that requires return, or when the FCU assembly requires overhaul, but not later than December 31,
overtorque, overtemperature, uncontained rotor failure, and asymmetric thrust in multi-engine 2012. Information on replacement FCU assembly P/Ns, configuration management, rework, and
airplanes. We are issuing this AD to prevent destructive overspeed that could result in uncontained replacement information, can be found in Honeywell ASB No. TPE331-A73-0262, Revision 2, dated
rotor failure, and damage to the airplane. June 17, 2005.
Compliance TPE331-10, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, -12UA, -12UAR,
and -12UHR Series Engines
(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. (j) For TPE331-10, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, -12UA, -
12UAR, and -12UHR series engines, replace Woodward FCU assemblies, P/Ns 897375-2/ -3/ -4/ -5/
Initial Inspection of Engines With Affected FCU Assemblies -8/ -9/ -10/ -11/ -12/ -13/ -14/ -15/ -16/ -17/ -19/ -21/ -24/ -25/ -26, and -27, and P/Ns 897780-1/ -2/ -
3/ -4/ -5/ -6/ -7/ -8/ -9/ -10/ -11/ -14/ -15/ -16/ -17/ -18/ -19/ -20/ -21/ -22/ -23/ -24/ -25/ -26/ -27/ -30/
(f) At the next scheduled inspection of the fuel control drive, but within 1,000 hours-in-service -32/ -34/ -36/ -37, and -38, and P/Ns 893561-17/ -18, and -19, with a serviceable, modified FCU
after the effective date of this AD: assembly the next time the FCU assembly is removed for cause that requires return, or when the FCU
(1) Perform an initial dimensional inspection of the fuel control drive for wear or damage. assembly requires overhaul, but not later than December 31, 2012. Information on replacement FCU
Information on spline inspection can be found in Section 72-00-00 of the applicable maintenance assembly P/Ns, configuration management, rework, and replacement information, can be found in
manuals. Honeywell ASB No. TPE331-A73-0254, Revision 2, dated June 17, 2005.
(2) Repair or replace the fuel pump, if the spline fails the dimensional inspection, with any
serviceable fuel pump. Definitions
(3) Repair or replace the FCU assembly, if the splines fail the dimensional inspection, with a
serviceable modified FCU assembly. (k) For the purposes of this AD:
(1) A ‘‘serviceable, modified FCU assembly'' for engines affected by paragraph (h), (i), or (j) of
Repetitive Inspections of Engines With Affected FCU Assemblies this AD, is an FCU assembly with a P/N not listed in this AD.
(2) The ‘‘fuel control drive'' is a series of mating splines located between the fuel pump and fuel
(g) Thereafter, within 1,000 hours since-last-inspection: control governor, consisting of the following four drive splines: The fuel pump internal spline, the
(1) Perform repetitive dimensional inspections of the fuel control drive, for wear or damage. fuel control external ‘‘quill shaft'' spline, and the stub shaft internal and external splines.
Information on spline inspection can be found in Section 72-00-00 of the applicable maintenance (3) A ‘‘removal for cause that requires return'', for engines affected by paragraph (h), (i), or (j) of
manuals. this AD, is an FCU assembly that has displayed an unserviceable or unacceptable operating condition
(2) Repair or replace the fuel pump, if the spline fails the dimensional inspection, with any requiring the FCU to be removed from service and sent to a repair or overhaul shop.
serviceable fuel pump.
(3) Repair or replace the FCU assembly if the splines fail the dimensional inspection, with a Optional Method of Compliance for TPE331 Series Engines Installed On Single-Engine
serviceable modified FCU assembly. Airplanes
TPE331-1, -2, and -2UA Series Engines (l) As an optional method of compliance to paragraph (h), (i), or (j) of this AD, for TPE331
series engines installed on single-engine airplanes, having an affected Woodward FCU assembly
(h) For TPE331-1, -2, and -2UA series engines, replace Woodward FCU assemblies, P/Ns perform the following steps as necessary:
869199-13/ -20/ -21/ -22/ -23/ -24/-25/ -26/ -27/ -28/ -29/ -31/ -32/ -33/ -34, and -35, with a (1) Continue repetitive dimensional inspections of the fuel control drive, for wear or damage as
serviceable, modified FCU assembly the next time the FCU assembly is removed for cause that specified in paragraph (g)(1) of this AD.
requires return, or when the FCU assembly requires overhaul, but not later than December 31, 2012. (2) Repair or replace the fuel pump or FCU assembly if the splines fail the dimensional
Information on replacement FCU assembly P/Ns, configuration management, rework, and inspection, with any serviceable fuel pump or FCU assembly.
replacement information, can be found in Honeywell Alert Service Bulletin (ASB) No. TPE331-A73-
0271, Revision 1, dated January 25, 2006. Terminating Action
(m) Performing an FCU assembly replacement as specified in paragraph (h), (i), or (j) of this
AD, is terminating action for the initial and repetitive inspections required by this AD.
7 8
Alternative Methods of Compliance Lufttüchtigkeitsanweisung
LTA-Nr.: D-2006-237
(n) The Manager, Los Angeles Aircraft Certification Office, has the authority to approve
alternative methods of compliance for this AD if requested using the procedures found in 14 CFR Luftfahrt-Bundesamt
39.19. Datum der Bekanntgabe: 21.08.2006
Muster: McCauley AD der ausländischen Behörde:
Related Information 5JFR36C FAA AD 2006-15-13 Amdt. 39-14693
Geräte-Nr.: Technische Mitteilungen des Herstellers:
(o) Information pertaining to operating recommendations for applicable engines after a fuel 32.130/85 McCauley Propellers Alert Service Bulletin ASB252 vom
control drive failure is contained in OI 331-12R5 dated July 10, 2006, for multi-engine airplanes and 06.06.2006
in OI 331-18R3 dated July10, 2006, for single-engine airplanes.
Betroffenes Luftfahrtgerät:
Issued in Burlington, Massachusetts, on July 14, 2006.
Francis A. Favara, McCauley
5JFR36C
Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. E6-11540 Filed 7-19-06; 8:45 am] - Baureihen: B5JFR36C1101/114GCA-0
B5JFR36C1103/114HCA-0
C5JFR36C1102/L114GCA-0
C5JFR36C1104/L114HCA-0
- Werk-Nrn.: Alle
Betrifft:
Möglicher Bruch von Propellerblättern durch Rißbildung.
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 2006-15-13 Amdt. 39-14693
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
***
9
Aktenzeichen: (11)T23-502.1/D-2006-237 Seite 1 von 1
[Federal Register: July 26, 2006 (Volume 71, Number 143)] FOR FURTHER INFORMATION CONTACT: Jeff Janusz, Aerospace Engineer, Wichita
[Rules and Regulations] Aircraft Certification Office, FAA, Small Airplane Directorate, 1801 Airport Road, Room 100,
[Page 42258-42260] Wichita, KS 67209, telephone: (316) 946-4148; fax: (316) 946-4107.
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26jy06-6] SUPPLEMENTARY INFORMATION: In May 2006, McCauley Propeller Systems received a
–––––––––––––––––––––––––––––––––––- report from an operator of two propeller blades found cracked during propeller overhaul. The
DEPARTMENT OF TRANSPORTATION propeller blades were installed on the same propeller assembly; on a ‘‘Jetstream 41'' airplane. The
cracks were located in the propeller blade retention groove, near the ledge where the split retainers
Federal Aviation Administration seat and on or near the shot peened surface of the retention groove. To date, no further reports of
these cracks have been received, and we know of no propeller blade failures due to these cracks. The
14 CFR Part 39 FAA is continuing to investigate, however, and we may issue further ADs based on the inspection
results reported to us under this AD. In order to assess the extent of any problem, we need to have all
[Docket No. FAA-2006-25173; Directorate Identifier 2006-NE-24-AD; Amendment 39-14693; the inspection results reported to us, even those showing that no crack indications were found. This
AD 2006-15-13] condition, if not corrected, could result in a failure and separation of the propeller blade and loss of
control of the airplane.
RIN 2120-AA64
Relevant Service Information
Airworthiness Directives; McCauley Propeller Systems Propeller Models
B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, and We have reviewed and approved the technical contents of McCauley Propellers Alert Service
C5JFR36C1104/L114HCA-0 Bulletin (ASB) ASB252, dated June 6, 2006. That ASB describes procedures for performing a
onetime FPI and ECI of propeller blades for cracks.
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
FAA's Determination and Requirements of This AD
ACTION: Final rule; request for comments.
The unsafe condition described previously is likely to exist or develop on other McCauley
–––––––––––––––––––––––––––––––––––- Propeller Systems propeller models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0,
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for McCauley Propeller B5JFR36C1103/114HCA-0, and C5JFR36C1104/L114HCA-0 of the same type design. For that
Systems propeller models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, reason, we are issuing this AD to detect cracks in the propeller blade that could cause failure and
B5JFR36C1103/114HCA-0, and C5JFR36C1104/L114HCA-0. This AD requires a onetime separation of the propeller blade and loss of control of the airplane. This AD requires for certain
fluorescent penetrant inspection (FPI) and eddy current inspection (ECI) of propeller blades for blades, a onetime FPI and ECI of propeller blades for cracks within 100 operating hours time-in-
cracks, and if any crack indications are found, removing the blade from service. This AD results from service after the effective date of the AD, and if any crack indications are found, removal from
a report of two propeller blades on the same propeller assembly, found cracked during propeller service. You must use the service information described previously to perform the actions required by
overhaul. We are issuing this AD to detect cracks in the propeller blade that could cause failure and this AD.
separation of the propeller blade and loss of control of the airplane.
FAA's Determination of the Effective Date
DATES: This AD becomes effective August 10, 2006. The Director of the Federal Register approved
the incorporation by reference of certain publications listed in the regulations as of August 10, 2006. Since an unsafe condition exists that requires the immediate adoption of this AD, we have found
We must receive any comments on this AD by September 25, 2006. that notice and opportunity for public comment before issuing this AD are impracticable, and that
good cause exists for making this amendment effective in less than 30 days.
ADDRESSES: Use one of the following addresses to comment on this AD:
DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your Interim Action
comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the These actions are interim actions and we may take further rulemaking actions in the future.
instructions for sending your comments electronically.
Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, Comments Invited
SW., Nassif Building, Room PL-401, Washington, DC 20590-0001.
Fax: (202) 493-2251. This AD is a final rule that involves requirements affecting flight safety and was not preceded by
Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, notice and an opportunity for public comment; however, we invite you to send us any written relevant
SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. data, views, or arguments regarding this AD. Send your comments to an address listed under
Contact McCauley Propeller Systems, 7751 East Pawnee, Wichita, KS 67277 for the service ADDRESSES. Include ‘‘AD Docket No. FAA-2006-25173; Directorate Identifier 2006-NE-24-D'' in
information referenced in this AD. the subject line of your comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might suggest a need to modify it.
1 2
We will post all comments we receive, without change, to http://dms.dot.gov, including any PART 39–AIRWORTHINESS DIRECTIVES
personal information you provide. We will also post a report summarizing each substantive verbal
contact with FAA personnel concerning this AD. Using the search function of the DMS Web site, 1. The authority citation for part 39 continues to read as follows:
anyone can find and read the comments in any of our dockets, including the name of the individual
who sent the comment (or signed the comment on behalf of an association, business, labor union, Authority: 49 U.S.C. 106(g), 40113, 44701.
etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register published
on April 11, 2000 (65 FR 19477-78) or you may visit http://dms.dot.gov. § 39.13 [Amended]
Examining the AD Docket 2. The FAA amends § 39.13 by adding the following new airworthiness directive:
You may examine the docket that contains the AD, any comments received, and any final
disposition in person at the Docket Management Facility Docket Offices between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647-5227) is
located on the plaza level of the Department of Transportation Nassif Building at the street address
stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives
them.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III,
section 44701, ‘‘General requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses an unsafe condition that is likely
to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States, on the relationship between the
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. Is not a ‘‘significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979); and
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.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Under the authority delegated to me by the Administrator, the Federal Aviation Administration
amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
3 4
Table 1.–Compliance Schedule
AIRWORTHINESS DIRECTIVE U.S. Department
of Transportation
www.faa.gov/aircraft/safety/alerts/ Federal Aviation If the propeller blade: Then inspect the propeller blade:
Administration (1) Has 1,200 operating hours or more time-in- Within 100 operating hours TIS after the
www.gpoaccess.gov/fr/advanced.html
service (TIS) and has not reached first overhaul.effective date of this AD.
2006-15-13 McCauley Propeller Systems: Amendment 39-14693. Docket No. FAA-2006-25173; (2) Has 1,000 operating hours or more TIS since Within 100 operating hours TIS after the
Directorate Identifier 2006-NE-24-AD. last overhaul effective date of this AD.
(3) Has fewer than 1,200 operating hours TIS Before the propeller blade reaches 1,300
Effective Date operating hours TIS.
(4) Has been overhauled but has fewer than 1,000 Upon reaching 1,100 operating hours TSO.
(a) This airworthiness directive (AD) becomes effective August 10, 2006. operating hours time-since-overhaul (TSO).
Affected ADs Propeller Blades Found Cracked
(b) None. (g) Remove from service propeller blades found with any crack indications.
Applicability Reporting Requirements
(c) This AD applies to McCauley Propeller Systems propeller models B5JFR36C1101/114GCA- (h) Within 10 calendar days of the inspection, use the Reporting Form for Service Bulletin 252 to
0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, and C5JFR36C1104/L114HCA-0. report all inspection findings to:
These propellers are installed on BAE Systems (Operations) Limited Jetstream Model 4100 and 4101 (1) The FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, KS
series airplanes (Jetstream 41). 67209, Attention: Jeff Janusz, telephone (316) 946-4148; FAX (316) 946-4107, e-mail:
jeff.janusz@faa.gov; and
Unsafe Condition (2) McCauley Propeller Systems, 7751 East Pawnee, Wichita, KS 67277.
(3) The Office of Management and Budget (OMB) has approved the reporting requirements and
(d) This AD results from a report of two propeller blades on the same propeller assembly, found assigned OMB control number 2120-0056.
cracked during propeller overhaul. We are issuing this AD to detect cracks in the propeller blade that
could cause failure and separation of the propeller blade and loss of control of the airplane. Alternative Methods of Compliance
Compliance (i) The Manager, Wichita Aircraft 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.
(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. Special Flight Permits
Onetime Propeller Blade Inspection (j) Under 39.23, we are limiting the availability of special flight permits for this AD. Special
flight permits are available only if:
(f) Perform a onetime fluorescent penetrant inspection and eddy current inspection of propeller (1) The operator has not seen signs of external oil leakage from the hub; and
blades, using the Equipment Required and Accomplishment Instructions of McCauley Propellers (2) The operator has not observed abnormal propeller vibration or abnormal engine vibration;
Alert Service Bulletin ASB252, dated June 6, 2006, using the following compliance schedule: and
(3) The operator has not observed any other abnormal operation from the engine or propeller;
and
(4) The operator has not made earlier reports of abnormal propeller vibration, abnormal engine
vibration, or other abnormal engine or propeller operations, that have not been addressed.
Related Information
(k) None.
5 6
Material Incorporated by Reference Lufttüchtigkeitsanweisung
LTA-Nr.: D-2006-238
(l) You must use McCauley Propeller Systems Alert Service Bulletin ASB252, dated June 6,
2006, to perform the inspections required by this AD. The Director of the Federal Register approved Luftfahrt-Bundesamt
the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR Datum der Bekanntgabe: 22.08.2006
part 51. Contact McCauley Propeller Systems, 7751 East Pawnee, Wichita, KS 67277, for a copy of Muster: Embraer (Brasilien) AD der ausländischen Behörde:
this service information. You may review copies at the FAA, New England Region, Office of the EMB-145 CTA BAD 2006-07-02 Amdt. 39-1147 vom 21.08.2006
Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Geräte-Nr.: Technische Mitteilungen des Herstellers:
Records Administration (NARA). For information on the availability of this material at NARA, call 2864 Embraer Service Bulletin No. 145LEG-28-0016 Rev. 01
202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Betroffenes Luftfahrtgerät:
Issued in Burlington, Massachusetts, on July 18, 2006.
Francis A. Favara, Embraer (Brasilien)
Manager, Engine and Propeller Directorate, Aircraft Certification Service. EMB-145
[FR Doc. E6-11799 Filed 7-25-06; 8:45 am]
- Baureihen: EMB-135BJ
- Werk-Nrn.: Alle
Betrifft:
Mangelhafte Isolation von Teilen der elektrischen Anlage hinsichtlich der Forderungen nach ''SFAR-88''.
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten CTA
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 CTA Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
CTA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
CTA BAD 2006-07-02 Amdt. 39-1147 vom 21.08.2006
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)T23-502.1/D-2006-238 Seite 1 von 1
CONTINUATION OF AD No.: 2006-07-02 - AMENDMENT 39-1147 PAGE No.: 2/2
For acquisition, contact:
National Agency of Civil Aviation (ANAC)
Publications Branch
R. Santa Luzia, 651, 2º Mezanino, Centro
REPÚBLICA FEDERATIVA DO BRASIL Fax: 55 (21) 3814-6929
AGÊNCIA NACIONAL DE AVIAÇÃO CIVIL – ANAC 20030-040 – Rio de Janeiro - RJ, BRAZIL.
e-mail: publicacoes@anac.gov.br
BRAZILIAN AIRWORTHINESS DIRECTIVE APPROVAL:
AD No.: 2006-07-02 Effective Date: 21 Aug. 2006 CLÁUDIO PASSOS SIMÃO
General Manager
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. 7,565 dated GGCP
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 this AD applies,
unless it has previously complied with the requirements established herein. MILTON ZUANAZZI
Director-President
AD No. 2006-07-02 - EMBRAER - Amendment 39-1147. ANAC
APPLICABILITY:
This Airworthiness Directive is applicable to Embraer EMB-135BJ aircraft model in operation. NOTE: Original in Portuguese language signed and available in the files of the Aeronautical Products
Certification Branch (GGCP) of the National Agency of Civil Aviation (ANAC).
CANCELLATION / REVISION:
Not applicable.
REASON:
It has been found cases in which some wiring harnesses were not protected in accordance with
SFAR-88 requirements.
Since this condition may exist in other airplanes of the same model and affects flight safety, a
corrective action is required. Thus, sufficient reason exists to request compliance with this AD in the indicated
time limit.
REQUIRED ACTION:
Installation of heat shrinkable sleeves and nipples to protect the wiring and their terminals.
COMPLIANCE:
Required as indicated below, unless already accomplished.
Within the next 5000 flight hours after the effective date of this AD, install heat shrinkable
sleeves on the inspection and refueling panel illumination lights wiring, as well as nipples to protect the wire
terminals.
The detailed instructions and procedures to accomplish this AD are described in the Embraer
Service Bulletin No. 145LEG-28-0016 Rev. 01, or further revisions approved by the ANAC.
Record compliance with this AD in the applicable maintenance log book.
CONTACT:
For additional technical information, contact:
National Agency of Civil Aviation (ANAC)
Aeronautical Products Certification Branch (GGCP)
Praça Mal. Eduardo Gomes, N° 50, Vila das Acácias (Prédio do CTA-IFI)
Fax: 55 (12) 3941-4766
12228-901 – São José dos Campos - SP, BRAZIL
E-mail: pds@ifi.cta.br
Form F-900-04D Form F-900-04D
Lufttüchtigkeitsanweisung
LTA-Nr.: D-2006-239
Luftfahrt-Bundesamt REPÚBLICA FEDERATIVA DO BRASIL
Datum der Bekanntgabe: 22.08.2006 AGÊNCIA NACIONAL DE AVIAÇÃO CIVIL – ANAC
Muster: Embraer (Brasilien) AD der ausländischen Behörde:
EMB-145 CTA BAD 2006-07-03 Amdt. 39-1148 vom 23.08.2006 BRAZILIAN AIRWORTHINESS DIRECTIVE
Geräte-Nr.: Technische Mitteilungen des Herstellers:
2864 Embraer Service Bulletin No. 145LEG-28-0022 AD No.: 2006-07-03 Effective Date: 23 Aug. 2006
The following Brazilian Airworthiness Directive (AD), issued by the Agência Nacional de Aviação Civil (ANAC)
Betroffenes Luftfahrtgerät: in accordance with provisions of Chapter IV, Title III of Código Brasileiro de Aeronáutica - Law No. 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 this AD applies,
Embraer (Brasilien) unless it has previously complied with the requirements established herein.
EMB-145
AD No. 2006-07-03 - EMBRAER - Amendment 39-1148.
- Baureihen: EMB-135BJ APPLICABILITY:
- Werk-Nrn.: Alle This Airworthiness Directive is applicable to Embraer aircraft EMB-135BJ model in operation.
CANCELLATION / REVISION:
Betrifft: Not applicable.
Brandgefahr durch Scheuerstellen am elektrischen Kabelbaum im Bereich der vorderen und hinteren
Zusatztanks. REASON:
It has been found the possibility of occurrence of sparks due to chaffing between the harnesses
Maßnahmen: of the forward and aft auxiliary fuel tanks, between some of these harnesses to the aircraft structure, or between
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten CTA some of these harnesses to some mechanical component, which may lead to a possible ignition source in the
Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen. vicinity of these fuel tanks.
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
vollständig und innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchge- Since this condition exists and affects flight safety, a corrective action is required. Thus,
führt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung sufficient reason exists to request compliance with this AD in the indicated time limit.
bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt. REQUIRED ACTION:
Rework, modification and re-identification of the aft and forward auxiliary fuel tanks.
Fristen:
Alle anzuwendenden Fristen sind der oben genannten CTA Airworthiness Directive zu entnehmen. COMPLIANCE:
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten Required as indicated below, unless already accomplished.
CTA Airworthiness Directive.
(a) Within the next 5000 flight hours after the effective date of this AD, carry out the modifications in the
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der forward auxiliary fuel tank according to items (1) thru (9) below:
CTA BAD 2006-07-03 Amdt. 39-1148 vom 23.08.2006 (1) Protect the low level switch harness using the hose protector bearing P/N AE208-4, and reroute its
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 harness and the fuel pumps A and B harnesses, as well;
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. (2) Install bonding jumper P/N PE88074-C004BB on pilot valve tubes assembly bearing P/N
135-02653-401 and 135-02654-401; reinstall bonding jumper P/N PE88074-C006BB; and install
Rechtsbehelfsbelehrung: bonding jumper P/N PE88074-C005BB (1 position) and PE88074-C006BB (1 position) together on
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. pilot lines tubes bearing P/N 135-05028-401 and 135-06425-401, on refuel/defuel tubes bearing P/N
135-05044-401 and 135-07980-401, and on existing holes of the forward auxiliary fuel tank rib 9;
LTAs werden auch im Internet unter http://www.lba.de publiziert
*** (3) Install bonding jumper P/N PE88074-C006BB (1 position) on vent line tube bearing P/N
135-07982-401 and on support of probe-fuel indicator bearing P/N 028-065-002;
(4) Install bonding jumper P/N PE88074-C006BB (1 position) on vent line tube bearing P/N
135-07982-401 and on existing hole of the forward auxiliary fuel tank rib 8;
(5) Reinstall bonding jumper P/N PE88074-006BB (3 positions) and install bonding jumper P/N
PE88074-004BB (2 positions) on pilot line tube bearing P/N 135-06425-401, on refuel/defuel tube
bearing P/N 135-07980-401, and on existing holes of the forward auxiliary fuel tank rib 8;
(6) Install bonding jumper P/N PE88074-006BB (2 positions) on transfer lines tubes bearing P/N
135-03513-402 and 135-035512-401, and on existing holes of the forward tank pump support;
(7) Install bonding jumper P/N PE88074-004BB (1 position) on transfer lines tubes bearing P/N
135-03513-402 and 135-03512-401;
Aktenzeichen: (01)T23-502.1/D-2006-239 Seite 1 von 1
Form F-900-04D
CONTINUATION OF AD No.: 2006-07-03 - AMENDMENT 39-1148 PAGE No.: 2/2
(8) Reinstall bonding jumper P/N PE88074-008BB and install bonding jumper P/N PE88074-008BB
(1 position) on refuel/defuel tube bearing P/N 135-05044-401, and on forward auxiliary fuel tank rib AIRWORTHINESS DIRECTIVES
10 support;
(9) Re-identify the forward auxiliary fuel tank installing a new placard bearing P/N PE16014-2. In the following, the Luftfahrt-Bundesamt publishes Airworthiness Directives referring to aeronautical products of
German production or to foreign aeronautical products for which the LBA on the basis of own findings arranged
(b) Within the next 5000 flight hours after the effective date of this AD, carry out the modifications in the aft for the issuance of an Airworthiness Directive. Only in the a.m. cases will Airworthiness Directives be translated
auxiliary fuel tanks (LH and RH sides), according to items (1) thru (6) below: and published in the following.
(1) Install new support assemblies bearing P/N 135-13605-401, 135-12331-401 and In accordance with § 14 of Aircraft Operations Order (NfL II-26/70) the following Airworthiness Directives (LTA’s)
135-13621-401 (LH side), and 135-13605-402, 135-12331-403 and 135-13621-402 (RH side); will be notified.
(2) Install the hose protection bearing P/N AE208-4 in the whole length of the low level sensor harness; After the effective date of an AD, an aeronautical product concerned by the AD may no longer be operated
(3) Reroute the electrical harnesses in the support assemblies bearing P/N 135-13605-401 and except for the purpose of accomplishment of the actions prescribed, until the prescribed actions have properly
been accomplished.
135-13621-401 (LH side), and 135-13605-402 and 135-13621-402 (RH side);
(4) Reroute the electrical harnesses in the support assembly bearing P/N 135-12331-401 (LH side) and The Service Bulletins issued by manufacturers are the reason for the publication of these ADs and thus become
135-12331-404 (RH side), on support assembly bearing P/N 135-13605-401 (LH side) and a constituent part of these Airworthiness Directives. We expressly point out that subsequent changes to the
Service Bulletins do not automatically belong to these ADs.
135-13605-402 (RH side), on support assembly bearing 135-13621-401 (LH side) and 135-13621-402
(RH side), and on tube assembly; Accomplishment and Log Book Entry:
The actions are to be accomplished and certified by an organisation approved in accordance with § 2 (2) No. 3 of
(5) Electrically bond the aft tank refuel solenoid valves and transfer solenoid valve support surfaces; and the Approval of Aeronautical Products Order (LuftGerPV). The regulations relating to the operating records to be
(6) Re-identify the aft auxiliary fuel tanks (LH and RH sides) installing a new placard bearing P/N kept in accordance with § 15 Aircraft Operations Order and JAR-OPS 1.920 (b) + (5) shall be adhered to.
PE16014-2.
The detailed instructions and procedures to accomplish this AD are described in the Embraer
Service Bulletin No. 145LEG-28-0022, original issue, or further revisions approved by the CTA.
AD-No. Title German Type Certificate No.
Record compliance with this AD in the applicable maintenance log book.
CONTACT: Amendments:
-none-
For additional technical information, contact:
National Agency of Civil Aviation (ANAC) New Issues:
Aeronautical Products Certification Branch (GGCP) -none-
Praça Mal. Eduardo Gomes, N° 50, Vila das Acácias (Prédio do CTA-IFI)
Fax: 55 (12) 3941-4766 LTA´s / AD´s and Technical Notes are published on the internet at http://www.lba.de
12228-901 – São José dos Campos - SP, BRAZIL
E-mail: pds@ifi.cta.br Note:
1) Please pay attention to the fact that in the title of an AD, the number is followed by the manufacturer’s
For acquisition, contact: normal name in short form (without indicating the legal form). It is the name of the type supporting
organisation competent at the date of the issue of the AD. In the future, former type support
National Agency of Civil Aviation (ANAC) organisations or manufacturers will no longer be indicated in the title of the AD. If there are doubts as to
Publications Branch the applicability of an AD, a check by means of the LBA Type Certificate Data Sheet should be
conducted. This number is indicated in the certification documents or on the type plate of the
R. Santa Luzia, 651, 2º Mezanino, Centro
aeronautical product.
Fax: 55 (21) 3814-6929
20030-040 – Rio de Janeiro - RJ, BRAZIL. 2) As a result of the EU-wide standardisation of Airworthiness Directives, the numbering system of German
e-mail: publicacoes@anac.gov.br ADs has been changed. All AD numbers hereafter will be preceded by the German country code ”D-”.
This change also applies to previous ADs to be changed from 01.01.2004 (e.g. D-2004-…, or D-1998-
APPROVAL: …). Revised ADs will be hereafter marked consecutively with “R” (Revision) (e.g. D-1998-…R1).
CLÁUDIO PASSOS SIMÃO
General Manager
GGCP
MILTON ZUANAZZI
Director-President
ANAC
NOTE: Original in Portuguese language signed and available in the files of the Aeronautical Products
Certification Branch (GGCP) of the National Agency of Civil Aviation (ANAC).
Form F-900-04D
