Nachrichten für Luftfahrer 2010 Teil II (weicht ggf. von Druckversion ab)
SUPPLEMENTARY INFORMATION: 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
Discussion 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.
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede
airworthiness directive (AD) 2005-24-08, Amendment 39-14388. (70 FR 71756, November 30, Regulatory Findings
2005). That AD applies to the specified products. That NPRM published in the Federal Register on
June 17, 2010 (75 FR 34390). That NPRM proposed to require: 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
• Removing from service the hub of any propeller assembly, P/N B5JFR36C1101/114GCA-0, national government and the States, or on the distribution of power and responsibilities among the
C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, or C5JFR36C1104/L114HCA-0, various levels of government.
if the hub exceeds 6,000 hours TSN on the effective date of this AD, within 250 hours time- For the reasons discussed above, I certify that this AD:
in-service (TIS) after the effective date of this AD. (1) Is not a ''significant regulatory action'' under Executive Order 12866,
• Removing from service the hub of any propeller assembly, P/N B5JFR36C1101/114GCA-0, (2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034,
C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, or C5JFR36C1104/L114HCA-0, February 26, 1979),
if the hub has fewer than 6,000 hours TSN, not later than 6,000 hours TSN. (3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or negative, on a substantial number of
Comments small entities under the criteria of the Regulatory Flexibility Act.
We gave the public the opportunity to participate in developing this AD. We received no List of Subjects in 14 CFR Part 39
comments on the NPRM or on the determination of the cost to the public.
Air transportation, Aircraft, Aviation safety, Safety.
Conclusion
Adoption of the Amendment
We reviewed the relevant data and determined that air safety and the public interest require
adopting the AD as proposed–except for minor editorial changes. We have determined that these Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part
minor changes: 39 as follows:
• Are consistent with the intent that was proposed in the NPRM for correcting the unsafe
condition; and PART 39–AIRWORTHINESS DIRECTIVES
• Do not add any additional burden upon the public than was already proposed in the NPRM.
1. The authority citation for part 39 continues to read as follows:
Costs of Compliance
Authority: 49 U.S.C. 106(g), 40113, 44701.
We estimate that this AD affects 30 engines installed on airplanes of U.S. registry.
We estimate the following costs to comply with this AD: § 39.13 [Amended]
Estimated costs 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2005-24-08, Amendment 39-
14388. (70 FR 71756, November 30, 2005), and adding the following new AD:
Cost per Cost on U.S.
Action Labor cost Parts cost
product operators
Remove the 42 work-hours X
propeller hub $85 per hour = $6,000 $9,570 $287,100
from service $3,570
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
2 3
Alternative Methods of Compliance
AIRWORTHINESS DIRECTIVE
FAA (i) The Manager, Wichita Aircraft Certification Office, has the authority to approve alternative
www.faa.gov/aircraft/safety/alerts/
Aviation Safety methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19.
www.gpoaccess.gov/fr/advanced.html
Related Information
2010-23-06 McCauley Propeller Systems: Amendment 39-16495; Docket No. FAA-2005-22690; (j) Contact Jeff Janusz, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, Small
Directorate Identifier 2005-NE-35-AD. Airplane Directorate, 1801 Airport Road, Room 100, Wichita, KS 67209, telephone: (316) 946-4148;
fax: (316) 946-4107, for more information about this AD.
Effective Date
Material Incorporated by Reference
(a) This airworthiness directive (AD) is effective December 8, 2010.
(k) None.
Affected ADs
Issued in Burlington, Massachusetts, on October 25, 2010.
(b) This AD supersedes AD 2005-24-08, Amendment 39-14388. Karen M. Grant,
Acting Assistant Manager, Engine & Propeller Directorate,
Applicability Aircraft Certification Service.
(c) This AD applies to McCauley Propeller Systems propeller assemblies, part numbers (P/Ns)
B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, and
C5JFR36C1104/L114HCA-0. These propeller assemblies are installed on BAE Systems (Operations)
Limited Jetstream Model 4100 series airplanes.
Unsafe Condition
(d) This AD results from a report of a cracked propeller hub. We are issuing this AD to prevent
cracked propeller hubs, which could cause failure of the propeller hub, blade separation, and loss of
control of the airplane.
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.
Propeller Hub Reduced Life Limits
(f) For any propeller assembly, P/N B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0,
B5JFR36C1103/114HCA-0, or C5JFR36C1104/L114HCA-0, with a hub that exceeds 6,000 hours
time-since-new (TSN) on the effective date of this AD, remove the propeller hub from service within
250 hours time-in-service after the effective date of this AD.
(g) For any propeller assembly, P/N B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0,
B5JFR36C1103/114HCA-0, or C5JFR36C1104/L114HCA-0, with a hub with fewer than 6,000 hours
TSN, remove the propeller hub from service not later than 6,000 hours TSN.
Prohibition of Hubs Exceeding Life Limit
(h) After the effective date of this AD, don't install any hub removed from any propeller
assembly that was removed by paragraphs (f) or (g) of this AD into any propeller assembly.
4 5
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig Transport Transports TP 7245E
D-2007-286R1 Fax: +49-531-2355-725 Canada Canada No.
email: ad@lba.de 1/2
CF-2007-21R1
Issue Date
Bell Datum der Bekanntgabe: 01.12.2010 30 November 2010
DRINGEND! AIRWORTHINESS DIRECTIVE
Betroffenes Luftfahrtgerät: The following airworthiness directive (AD) may be applicable to an aircraft which our records indicate is registered in your name. ADs are issued pursuant to Canadian
Aviation Regulation (CAR) 521 Division X. Pursuant to CAR 605.84 and the further details of CAR Standard 625, Appendix H, the continuing airworthiness of a Canadian
Art des Luftfahrtgerätes: Drehflügler registered aircraft is contingent upon compliance with all applicable ADs. Failure to comply with the requirements of an AD may invalidate the flight authorization of the aircraft.
Alternative means of compliance shall be applied for in accordance with CAR 605.84 and the above-referenced Standard.
Inhaber der Musterzulassung: Bell Helicopter Textron Canada This AD has been issued by the Continuing Airworthiness Division (AARDG), National Aircraft Certification Branch, Transport Canada, Ottawa, telephone 613 952-4357.
Hersteller: Bell Helicopter Textron Canada
Muster: Bell 206, Bell 222 URGENT URGENT URGENT URGENT URGENT URGENT URGENT URGENT URGENT
Baureihen: 206A, 206B, 206L, 206L-1, 206L-3, 206L-4, 222, 222B, 222U, 230, 407, 427
und 430 TRANSPORT CANADA EMERGENCY AIRWORTHINESS DIRECTIVE
Werknummern: Nähere Angaben über betroffene Helikopter sind den genannten Alert Service PLEASE FORWARD IMMEDIATELY TO THE PERSON RESPONSIBLE FOR THE OPERATION
Bulletins des Herstellers zu entnehmen. AND MAINTENANCE OF YOUR AIRCRAFT
Gerätenummer: 3034, 3054
Revisionsstand: Number: CF-2007-21R1
Diese LTA ersetzt D-2007-286 vom 14.09.2007
Subject: Tail Rotor Blades
Airworthiness Directive der ausländischen Behörde:
TC Emergency AD CF-2007-21R1 vom 30.11.2010
Effective: Upon receipt
Betrifft:
Möglicher Verlust der Steuerbarkeit des Helikopters durch Loslösung von Auswuchtgewichten am Heckrotor. Revision: Supersedes Airworthiness Directive CF-2007-21
Maßnahmen und Fristen: Applicability: Bell Helicopter Textron Canada (BHTC) helicopter Models:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten Transport Canada (TC)
206A, 206B, 206L, 206L-1, 206L-3, 206L-4, 222, 222B, 222U, 230, 407, 427
Airworthiness Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen. Alle
erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und and 430
innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Compliance: Before next flight unless already accomplished.
Zustimmung durch das Luftfahrt-Bundesamt.
Background: There were three reports of balance weights departing from the tail rotor
Alle anzuwendenden Fristen sind der genannten TC Airworthiness Directive zu entnehmen. Die Laufzeit aller
blades during flight. The cause has been narrowed down to missing weight
anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten TC Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der screws. This failure can happen at any time. This condition, if not corrected,
TC Emergency AD CF-2007-21R1 vom 30.11.2010. could lead to loss of control of the helicopter.
Since the issuance of the original directive, the blade manufacturer has
Zugehörige technische Dokumente: determined that a batch of additional blades could be affected. This revision
1. Bell Helicopter Textron Alert Service Bulletin 206-07-116 Revision B vom 29.11.2010 extends applicability of this directive to cover the affected blades.
2. Bell Helicopter Textron Alert Service Bulletin 206L-07-148 Revision B vom 29.11.2010
3. Bell Helicopter Textron Alert Service Bulletin 222-07-106 Revision D vom 29.11.2010 Corrective Verify if the affected blades are installed on the helicopter as per applicable
4. Bell Helicopter Textron Alert Service Bulletin 222U-07-77 Revision D vom 29.11.2010 Actions: Alert Service Bulleting (ASB) listed below, or later revisions approved by
5. Bell Helicopter Textron Alert Service Bulletin 230-07-38 Revision D vom 29.11.2010 Chief, Continuing Airworthiness, Transport Canada. Remove the affected
6. Bell Helicopter Textron Alert Service Bulletin 407-07-81 Revision B vom 29.11.2010
blades before further flight and replace with airworthy parts.
7. Bell Helicopter Textron Alert Service Bulletin 427-07-18 Revision B vom 29.11.2010
8. Bell Helicopter Textron Alert Service Bulletin 430-07-41 Revision D vom 29.11.2010
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der Sicherheit des Luftverkehrs, das in diesem Fall Pursuant to CAR 202.51 the registered owner of a Canadian aircraft shall, within seven days, notify the Minister
das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es erforderlich, die sofortige Vollziehung dieser Lufttüchtigkeitsanweisung in writing of any change of his or her name or address.
anzuordnen. To request a change of address, contact the Civil Aviation Communications Centre (AARC)
Rechtsbehelfsbelehrung: at Place de Ville, Ottawa, Ontario K1A 0N8, or 1-800-305-2059,
or www.tc.gc.ca/civilaviation/communications/centre/ address.asp
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. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge- 24-0022 (01-2005)
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
D-2007-286R1 Seite 1 von 1 577/2010
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig
No.
Nq
CF-2007-21R1 2/2 D-2009-242R1 Fax: +49-531-2355-725
email: ad@lba.de
TURBOMECA Datum der Bekanntgabe: 30.11.2010
Helicopter Alert Service Bulletin Date
Model Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
206A 206-07-116 Rev.B 29 November 2010 Inhaber der Musterzulassung: TURBOMECA
206B 206-07-116 Rev.B 29 November 2010 Hersteller: Turbomeca S.A.
Muster: ARRIEL 2
206L 206L-07-148 Rev.B 29 November 2010 Baureihen: ARRIEL 2B, 2B1 und 2B1A
Werknummern: Alle Triebwerke dieser Baureihen gemäß Turboméca Mandatory Service
206L-1 206L-07-148 Rev.B 29 November 2010 Bulletin (MSB) A292 73 2836 Version A und (MSB) A292 73 2830 Version B.
206L-3 206L-07-148 Rev.B 29 November 2010 Gerätenummer: 7003, EASA.E.001
206L-4 206L-07-148 Rev.B 29 November 2010 Revisionsstand:
Diese LTA ersetzt D-2009-242 vom 14.09.2009
222 222-07-106 Rev.D 29 November 2010
222B 222-07-106 Rev.D 29 November 2010 Airworthiness Directive der ausländischen Behörde:
EASA AD 2010-0215 vom 14.10.2010
222U 222U-07-77 Rev.D 29 November 2010
Betrifft:
230 230-07-38 Rev.D 29 November 2010 Engine Fuel & Control – HP/LP Pump Metering Unit – Low Pressure Fuel Pump Impeller Drive – Inspection/
407 407-07-81 Rev.B 29 November 2010 Replacement
427 427-07-18 Rev.B 29 November 2010 Maßnahmen und Fristen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten EASA Airworthiness
430 430-07-41 Rev.D 29 November 2010 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
Authorization: For Minister of Transport, Infrastructure and Communities den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das
Luftfahrt-Bundesamt.
ORIGINAL SIGNED BY Alle anzuwendenden Fristen sind der genannten EASA Airworthiness Directive zu entnehmen. Die Laufzeit aller
anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten EASA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
Robin Lau for EASA AD 2010-0215 vom 14.10.2010.
Derek Ferguson
Chief, Continuing Airworthiness
Zugehörige technische Dokumente:
1. Turbomeca Mandatory Service Bulletin A292 73 2830 Version B vom 10.07.2009
Contact: Mr. Bogdan Gajewski, Continuing Airworthiness, Ottawa, telephone 2. Turbomeca Mandatory Service Bulletin A292 73 2836 Version A vom 17.08.2010
613-952-4357, facsimile 613-996-9178 or e-mail
CAWWEBFeedback@tc.gc.ca or any Transport Canada Centre.
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men 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 Lufttüchtigkeitsanweisung
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. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge-
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
D-2009-242R1 Seite 1 von 1 511/2010
EASA AD No.: 2010-0215 EASA AD No.: 2010-0215
pump shaft, to prevent any detachment of the LP fuel pump impeller from
EASA AIRWORTHINESS DIRECTIVE the HP fuel pump shaft. AD 2009-0184 did not apply to HP/LP Pump
Metering Units which incorporate TU147 because this modification was
AD No.: 2010-0215 specifically designed to prevent uncoupling.
Since issuance of AD 2009-0184, three additional cases of uncoupling of
the LP fuel pump impeller and the HP fuel pump shaft have been
encountered in service with post-TU147 configuration. The results of the
Date: 14 October 2010 investigation show a significant scattering in the bonding process of the LP
fuel pump impeller on the HP fuel pump shaft. However the capability of
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with the modification TU147, if properly performed, to improve the coupling
Regulation (EC) No 216/2008 on behalf of the European Community, its Member States between LP fuel pump impeller and HP fuel pump shaft, is still believed to
and of the European third countries that participate in the activities of EASA under Article
66 of that Regulation. be adequate.
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301,
In response to these findings an improvement (with new qualification) and
the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person a reinforced control of the bonding manufacturing scheme have been
may operate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise implemented in all Turboméca production sites with a completion date of
specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 31 March 2010.
216/2008, Article 14(4) exemption].
This AD, which supersedes EASA AD 2009-0184, partially retaining its
Type Approval Holder’s Name : requirements, requires an inspection of certain HP/LP Pump Metering Units
Type/Model designation(s) :
post-TU147 to ensure that the LP fuel pump impeller is correctly driven by
Turboméca the HP fuel pump shaft to prevent any uncoupling. It also requires
ARRIEL 2 series turboshaft engines replacement of HP/LP Pump Metering Units, in case of discrepancies.
(1) TU147 modification consists of bonding the LP fuel pump impeller with the impeller screw.
TCDS Number : EASA.E.001
Effective Date: 28 October 2010
Foreign AD : Not applicable
Required Action(s) Required as indicated, unless accomplished previously:
Supersedure : This AD supersedes EASA AD 2009-0184 dated 14 August 2009 and Compliance
(1) Within the compliance time indicated in Table 1 of this AD, accomplish
Time(s):
the inspection and, in case of discrepancies, replace the HP/LP pump
metering unit, in accordance with the applicable Turboméca Mandatory
Engine Fuel & Control – High Pressure (HP)/Low Pressure (LP) Service Bulletins (MSBs).
ATA 73 Pump Metering Unit – Low Pressure Fuel Pump Impeller Drive (2) Replacement of the HP/LP Pump Metering Units with a serviceable one
– Inspection/Replacement constitutes a terminating action for the requirements of this AD.
(3) After the effective date of this AD, do not install HP/LP Pump Metering
Units unless in compliance with the requirements of this AD.
Manufacturer(s): Turboméca S.A.
Ref. Publications: Turboméca MSB A292 73 2830 version B dated 10 July 2009.
Applicability: Arriel 2B, 2B1, 2B1A turboshaft engines with applicability defined in
Turboméca Mandatory Service Bulletin (MSB) A292 73 2836 version A and Turboméca MSB A292 73 2836 version A dated 17 August 2010.
Turboméca Mandatory Service Bulletin (MSB) A292 73 2830 version B. The use of later approved revisions of these documents is acceptable for
These engines are known to be installed on, but not limited to: compliance with the requirements of this AD.
Eurocopter AS 350 B3, EC 130 B4 helicopters and Changhe Z11 Remarks : 1. If requested and appropriately substantiated, EASA can approve
helicopters. Alternative Methods of Compliance for this AD.
2. This AD was posted on 13 September 2010 as PAD 10-099 for
Reason: Several events of uncoupling of the LP (Low Pressure) fuel pump impeller consultation until 11 October 2010. No comments were received
and the HP (High Pressure) fuel pump shaft have been reported on during the consultation period.
1
ARRIEL 2 engines which do not incorporate modification TU147 ( ). In
most cases the “low fuel pressure switch” enlightened, the pilot activated 3. Enquiries regarding this AD should be referred to the Airworthiness
the aircraft booster pump in accordance with the Flight Manual Instructions Directives, Safety Management & Research Section, Certification
and landed safely with no other incident. One case, on a single-engine Directorate, EASA. E-mail: ADs@easa.europa.eu.
helicopter, led to a sudden engine power loss. 4. For any question concerning the technical content of the requirements
in this AD, please contact:
The uncoupling of the LP fuel pump impeller and the HP fuel pump shaft
may lead to a limitation of engine power or, at worst, an uncommanded In- Turboméca, S.A.
Flight Shut-Down (IFSD). On a single-engine helicopter, the result may be ARRIEL 2 Customer Support
an emergency autorotation landing. 40220 Tarnos, France
Fax: +33 5 59 74 45 15 or your usual or nearest Turboméca technical
For the reasons stated above, AD 2009-0184 was issued to require representative at www.turbomeca-support.com
ensuring that the LP fuel pump impeller was correctly driven by the HP fuel
EASA Form 110 Page 1/3 EASA Form 110 Page 2/3
EASA AD No.: 2010-0215 Luftfahrt-Bundesamt
Lufttüchtigkeitsanweisung
T23 LTA-Sachgebiet
Appendix to AD 2010-0215 38144 Braunschweig
D-2010-162R1 Fax: +49-531-2355-725
email: ad@lba.de
Table 1: HP/LP Pump Metering Unit Inspection and Replacement Requirements
ROLLS-ROYCE TURBOMECA Datum der Bekanntgabe: 02.12.2010
Condition Inspection Compliance Time for Action to be
the inspection accomplished Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: ROLLS-ROYCE TURBOMECA Ltd
Hersteller: ROLLS-ROYCE TURBOMECA Ltd
If no discrepancies are
Muster: RTM 322-01/9, RTM 322-01/9A
found, apply the
Baureihen: RTM 322-01/9 und RTM 322-01/9A
nominal tightening
Werknummern: Alle
Check the transmissible Within 500 Engine Flight torque to the screw of
Gerätenummer: EASA.E.009
torque between the LP Hours (EFH) after 28 the LP pump impeller
HP/LP Pump Metering pump impeller and the August 2009 [effective
Revisionsstand:
Units which do not HP pump shaft in date of EASA AD 2009- If discrepancies are Diese LTA ersetzt D-2010-162 vom 15.06.2010
incorporate modification accordance with 0184] but no later than found, before next flight,
TU147 paragraph 2 of 30 June 2010 [original replace the HP/LP Airworthiness Directive der ausländischen Behörde:
Turboméca MSB A292 compliance date of Pump Metering Unit EASA AD 2010-0228 vom 03.11.2010
73 2830 version B EASA AD 2009-0184] with a serviceable pre-
TU147 unit or a Betrifft:
serviceable post-TU147 Engine - M01 Compressor - Second Stage Compressor Axial Wheel and Impeller – Inspection
unit
Maßnahmen und Fristen:
HP/LP Pump Metering If no discrepancies are Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten EASA Airworthiness
Units which incorporate found, no further actions Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen. Alle erforderlichen
modification TU147 Check the transmissible are required for Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und innerhalb der
and torque between the LP compliance with the vorgesehenen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle Abweichungen von
Within 750 EFH after
pump impeller and the requirements of this AD den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das
the effective date of this
on which modification HP pump shaft in Luftfahrt-Bundesamt.
AD, but no later than 14
TU 147 was applied accordance with If discrepancies are
months after the
before or on 31 March paragraph 2 of found, before next flight, Alle anzuwendenden Fristen sind der genannten EASA Airworthiness Directive zu entnehmen. Die Laufzeit aller
effective date of this AD
2010, and are not listed Turboméca MSB A292 replace the HP/LP anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten EASA Airworthiness Directive.
in Figures 2 and 3 of 73 2836 version A Pump Metering Unit Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
Turboméca MSB A292 with a serviceable post- EASA AD 2010-0228 vom 03.11.2010.
73 2836 version A TU147 unit
Zugehörige technische Dokumente:
1. ROLLS-ROYCE TURBOMECA Ltd Emergency Mandatory Service Bulletin SBP-M3-A-71-00-00-05A-A-A Issue
number 001
2. ROLLS-ROYCE TURBOMECA Ltd Emergency Mandatory Service Bulletin SBP-M3-A-72-31-00-05A-A-A Issue
number 002
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men 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 Lufttüchtigkeitsanweisung
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. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge-
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
EASA Form 110 Page 3/3
D-2010-162R1 Seite 1 von 1 541/2010
EASA AD No : 2010–0228 EASA AD No : 2010–0228
Following issuance of EASA AD 2010-0114-E, Rolls Royce Turbomeca
EASA AIRWORTHINESS DIRECTIVE Ltd has completed further investigations and the results show that the
most probable scenario explaining blade cracks/rupture is as follows:
AD No.: 2010-0228 - Compressor blade tip rubbing on compressor casing potentially
generates a crack (possibly leading to blade rupture).
- This blade tip rubbing is the result of gas generator spool bending due to
extended stator lab seal rubbing which causes local overheating on curvic-
Date: 03 November 2010
couplings.
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with The crack initiation is believed to occur during engine start, resulting in a
Regulation (EC) No 216/2008 on behalf of the European Community, its Member States hung start below ground Idle.
and of the European third countries that participate in the activities of EASA under Article
66 of that Regulation. Note 1: “stagnation at start”, in the referenced ROLLS-ROYCE
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, TURBOMECA Ltd Emergency Mandatory Service Bulletins and
the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person defined in Emergency Mandatory Service Bulletin SBP-M3-A-71-
may operate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise 00-00-05A-A-A, is a particular type of “hung start” and is defined
specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC as follows:
216/2008, Article 14(4) exemption].
Type/Model designation(s) : - T46 increase, confirming combustion chamber light-off, and
Type Approval Holder’s Name :
RTM 322-01/9 and RTM 322-01/9A - engine stabilises at a constant speed below 50% NG and at
ROLLS-ROYCE TURBOMECA Ltd
turboshaft engines constant T46 for more than 10 seconds.
“Hung start” as used herein implies these same characteristics.
TCDS Number : EASA E.009 Based on the above scenario, this AD, which supersedes EASA AD
2010-0114-E, partially retaining its requirements, requires checking the
engine records to determine if a hung start occurred during the life of the
Foreign AD : Not applicable
engine, and, depending on the outcome of the record checks,
accomplishment of repetitive borescope inspections. Furthermore, it
Supersedure : This AD supersedes EASA AD 2010-0114-E dated 14 June 2010. precludes further engine operation in the event of a hung start, or if any
evidence of cracks anywhere on blades and/or rubs on axial wheel blade
tips is detected. This AD also requires the accomplishment of the
applicable corrective actions.
Engine - M01 Compressor - Second Stage Compressor Axial
ATA 72
Wheel and Impeller – Inspection Effective Date: 17 November 2010
Required action(s) Required as indicated, unless accomplished previously:
Manufacturer(s): Rolls-Royce Turbomeca Ltd and Compliance
(1) Within 10 days after the effective date of this AD, check the engine
Time(s):
records to identify any hung start occurrence in the engine operational
Applicability: RTM 322-01/9 and RTM 322-01/9A turboshaft engines, all serial numbers. history.
These engines are known to be installed on, but not limited to, NH (2) If a hung start is found, engine operation is not allowed. Contact the
Industries NH90 (military) helicopters. engine manufacturer for further instructions and accomplish them
accordingly.
Reason: There have been three incidents on RTM 322-01/9 and RTM 322-01/9A (3) If a hung start is experienced after the effective date of this AD,
turboshaft engines installed in NH90 helicopters, causing two engine In- engine operation is not allowed. Contact the engine manufacturer for
Flight Shut-Downs (IFSD) and one engine Shut-Down on ground. further instructions and accomplish them accordingly.
Strip inspections of the involved engines showed similar damage in all (4) Within the applicable compliance time as indicated in the table of the
three cases. Appendix to this AD, accomplish a borescope inspection of the
- Second stage compressor axial wheel: cracks on adjacent blades or second stage compressor axial wheel and impeller, and inspect each
partial/complete loss of adjacent blades. second stage compressor axial wheel blade tip, in accordance with
the Accomplishment Instructions of ROLLS-ROYCE TURBOMECA
- Impeller: crack and/or partial loss of one leading edge fragment. Ltd Emergency Mandatory Service Bulletin SBP-M3-A-72-31-00-05A-
Such damage, if not detected and corrected, could lead to further in-flight A-A.
shutdowns. (5) Repeat the borescope inspection of the second stage compressor
For the reason stated above, EASA EAD 2010-0114-E required repetitive axial wheel and impeller, and the inspection of each second stage
borescope inspections of the second stage compressor axial wheel and axial wheel blade tip, at the intervals described in the table of the
centrifugal impeller. Furthermore, it precluded further engine operation if Appendix to this AD and in accordance with the Accomplishment
any evidence of cracks anywhere on blades and/or rubs on axial wheel Instructions of ROLLS-ROYCE TURBOMECA Ltd Emergency
blade tips was detected. Mandatory Service Bulletin SBP-M3-A-72-31-00-05A-A-A.
EASA Form 110 Page 1/4 EASA Form 110 Page 2/4
EASA AD No : 2010–0228 EASA AD No : 2010–0228
(6) If the results of the inspections required by this AD show signs of
blade tip rubs or blade cracks, engine operation is not allowed. APPENDIX to EASA AD 2010-0228
Contact the engine manufacturer for further instructions and
accomplish them accordingly.
(7) Any Compressor Module (M01) installed in an engine after the
effective date of this AD must comply with the requirements of this AD. Records show that the engine has not experienced a hung start during a continuous period
ending at the effective date of this AD. During that continuous period, the engine
accumulated X EFH (Engine Flight Hours) and Y ES (Engine Starts). The beginning of the
Ref. Publications: ROLLS-ROYCE TURBOMECA Ltd Emergency Mandatory Service continuous period may be before entry into service, taking into account bench pass-off test
Bulletin SBP-M3-A-72-31-00-05A-A-A Issue number 002. and helicopter/engine history, provided that relevant records exist. If no relevant records exist,
or if the engine has not been in service since new or since last repair, then X = 0 and Y = 0.
ROLLS-ROYCE TURBOMECA Ltd Emergency Mandatory Service Repetitive Inspection
Bulletin SBP-M3-A-71-00-00-05A-A-A Issue number 001. Engine History Initial Inspection
Intervals
The use of later approved revisions of these documents is acceptable for As applicable, either: Not exceeding 5 EFH or 4
compliance with the requirements of this AD. ES, whichever occurs first,
within 5 EFH or 4 ES from until the engine accumulates
Remarks : 1. If requested and appropriately substantiated, EASA can approve the last inspection performed both (25-X) EFH and (20-Y)
Alternative Methods of Compliance for this AD. in accordance with EASA AD ES after the effective date of
2010-0114-E, whichever this AD. Then not exceeding
2. This AD was posted on 29 September 2010 as PAD 10-105 for occurs first; 30 EFH or 25 ES, whichever
consultation until 27 October 2010. No comments were received occurs first, until the engine
during the consultation period. X 25 or Y 20 or: accumulates both (115-X)
3. Enquiries regarding this AD should be referred to the Airworthiness EFH and (100-Y) ES after the
Directives, Safety Management & Research Section, Certification if no inspections were effective date of this AD.
Directorate, EASA. E-mail: ADs@easa.europa.eu. performed in accordance Thereafter, no further
with EASA AD 2010-0114-E, inspection is required for
4. For any question concerning the technical content of the requirements within 5 EFH or 4 ES after 16 compliance with the
in this AD, please contact: June 2010 (the effective date requirements of this AD.
your usual or nearest TURBOMECA technical representative (refer to of EASA AD 2010-0114-E),
http://www.turbomeca-support.com). whichever occurs first
As applicable, either: Not exceeding 30 EFH or 25
ES, whichever occurs first,
within 30 EFH or 25 ES from until the engine accumulates
the last inspection performed both (115-X) EFH and (100-
in accordance with EASA AD Y) ES after the effective date
2010-0114-E, whichever of this AD. Thereafter, no
occurs first; further inspection is required
for compliance with the
X > 25 and Y > 20 or: requirements of this AD.
if no inspections were
performed in accordance
with EASA AD 2010-0114-E,
within 30 EFH or 25 ES after
16 June 2010 (the effective
date of EASA AD 2010-0114-
E), whichever occurs first
Note 2: The parameters X and Y are introduced to allow credit for a continuous period, ending at the
effective date of this AD, during which no hung starts were recorded.
Note 3: 115 EFH / 100 ES is the maximum usage following a hung start, presumed unrecorded, during which
the symptoms identified by the borescope inspections are expected to develop. Thereafter, it is
assumed that no unrecorded hung start occurred or will occur.
EASA Form 110 Page 3/4 EASA Form 110 Page 4/4
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig
D-2010-304R2 Fax: +49-531-2355-725 EMERGENCY
email: ad@lba.de
FAA AIRWORTHINESS DIRECTIVE
Aviation Safety
BELL Datum der Bekanntgabe: 25.11.2010 www.faa.gov/aircraft/safety/alerts/
DRINGEND!
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler DATE: November 24, 2010
Inhaber der Musterzulassung: Bell Helicopter Textron AD #: 2010-25-51
Hersteller: Bell Helicopter Textron
Muster: Bell 212 Background
Baureihen: Bell 212
Werknummern: Alle
This EAD supersedes EAD 2010-24-52, issued November 19, 2010, and is prompted by the
Es sind alle Hubschrauber betroffen, die mit einem ''Main Rotor Hub Inboard need to require performing a magnetic particle inspection (MPI) on additional serial-numbered main
Strap Fitting'' der Part-Nummer (P/N) 212-010-103-007 ausgerüstet sind und rotor hub inboard strap fittings.
der "Inboard Strap Fitting" eine der folgenden Serial-Nummern (S/N) hat:
On November 12, 2010, we issued EAD 2010-24-51 for all Bell Model 212 helicopters with a
A-9956 bis A-10005, SH-52, SH-54, SH-55, SH-57 bis SH-65, SH-67, SH-69, main rotor hub inboard strap fitting (fitting), part number (P/N) 212-010-103-007, serial number
SH-70, SH-71, SH-73, SH-103, SH-112, SH-113, SH-137 und SH-139,
A-009911 bis A-009955, A-010006 bis A-010049, A-010075 bis A-010174,
(S/N) 9956 through 10005 with a prefix of “A.” That EAD required, before further flight, removing
A-010455 bis A-010460, A-010581 bis A-010655, A-010742 bis A-010791 any affected fitting and replacing it with an airworthy fitting. That EAD also prohibited installing
und A-010862 bis A-010946. any affected fitting on any helicopter. EAD 2010-24-51 was prompted by an accident that resulted in
several fatalities. During the investigation of the accident, a crack was found on the fitting.
Gerätenummer: 3039 Subsequently, four additional fittings from the same manufacturing lot were inspected and two were
Revisionsstand:
found to exhibit the same type of cracking. We issued EAD 2010-24-51 to prevent a cracked fitting,
Diese LTA ersetzt D-2010-304R1 vom 22.11.2010 which could result in failure of the fitting, loss of a main rotor blade, and subsequent loss of control
of the helicopter.
Airworthiness Directive der ausländischen Behörde:
FAA Emergency AD 2010-25-51 vom 24.11.2010 After we issued EAD 2010-24-51, additional fittings from a different manufacturing lot were
found to have the same type of crack as that found on the fitting involved in the accident. Therefore,
Betrifft:
(ATA 62) Rotors - Main Rotor Hub Inboard Strap Fitting - Removal / MPI-Inspection
on November 19, 2010, we issued superseding EAD 2010-24-52 to require the same actions as EAD
2010-24-51 but to expand the applicability to include additional fittings, S/N 9956 through 10005,
Maßnahmen und Fristen: with a prefix of “A” and S/N 52, 54, 55, 57 through 65, 67, 69, 70, 71, 73, 103, 112, 113, 137, and
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten FAA Airworthiness Directive 139, with a prefix of “SH.”
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 EADs 2010-24-51 and 2010-24-52 were issued as interim actions to address a known unsafe
auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle Abweichungen von den Maßnahmen und
Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt. condition. Bell is continuing to investigate the cause of the cracking. Because the root cause of the
cracking has not been determined and due to the severity of a fitting failure, we are superseding EAD
Alle anzuwendenden Fristen sind der genannten FAA Airworthiness Directive zu entnehmen. Die Laufzeit aller 2010-24-52 to continue to require replacing certain serial-numbered fittings and to require
anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten FAA Airworthiness Directive. performing an MPI on other serial-numbered fittings. We have determined that the MPI is necessary
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der to detect a crack on those fittings not already removed from service.
FAA Emergency AD 2010-25-51 vom 24.11.2010.
Relevant Service Information
Zugehörige technische Dokumente:
1. Bell Helicopter Alert Service Bulletin No. 212-10-141 Revision A vom 18.11.2010
2. Bell Helicopter Alert Service Bulletin No. 212-10-142 vom 24.11.2010 We reviewed Bell Alert Service Bulletin No. 212-10-141, Revision A, dated November 18,
2010 (ASB 212-10-141), which incorporates additional serial numbers (S/Ns) of the affected fittings,
and specifies the immediate removal of these subject serial-numbered fittings from service. Bell
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet. states they have determined that the fitting may not have been manufactured in accordance with the
Begründung
engineering design requirements and may fracture as a result of the non-conformance. Bell further
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom- states that their investigation is ongoing, and indicates that the ASB affects the fitting, P/N 212-010-
men 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 Lufttüchtigkeitsanweisung 103-007, S/Ns as listed in Table 1:
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. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge-
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
1
D-2010-304R2 Seite 1 von 1 570/2010
Table 1 - S/Ns in ASB 212-10-141 AD Requirements
A-9956 through A-10005 This EAD supersedes AD 2010-24-52 and requires the following:
SH-52, SH-54, SH-55 x Before further flight, for any helicopter with a fitting, S/N 9956 through 10005, with a
prefix of “A”; and S/N 52, 54, 55, 57 through 65, 67, 69, 70, 71, 73, 103, 112, 113, 137, and 139,
SH-57 through SH-65 with a prefix of “SH”, replace the fitting with an airworthy fitting. Any fitting with a S/N identified
in this paragraph of this EAD is no longer eligible for installation on any helicopter.
SH-67, SH-69, SH-70, SH-71, SH-73
x Before further flight, for any helicopter with a fitting, S/N 9911 through 9955, 10006
SH-103, SH-112, SH-113, SH-137, SH-139 through 10049, 10075 through 10174, 10455 through 10460, 10581 through 10655, 10742 through
10791, and 10863 through 10946, with a prefix of “A”, perform a magnetic particle inspection (MPI)
We have also reviewed Bell Alert Service Bulletin No. 212-10-142, dated November 24, 2010 of each fitting for a crack. If the fitting is cracked, replace it with an airworthy fitting. If the fitting is
(ASB 212-10-142), which specifies within the next 15 flight hours after release of the ASB, but no not cracked, reidentify the fitting in accordance with the specified portion of ASB 212-10-142. Also,
later than January 15, 2011, performing a one time MPI of the fitting, P/N 212-010-103-007, S/Ns as within 24 hours after finding any fitting with a crack doing any magnetic particle inspection, report
listed in Table 2: the information requested in Appendix 1 of this AD to the Manager, Rotorcraft Certification Office.
Table 2 – S/Ns in ASB 212-10-142 Differences Between This EAD and the Service Information
This EAD differs from the ASBs in that we do not require returning parts to Bell. Also, this
EAD differs from ASB 212-10-142 in that we:
A-009911 through A-009955
x Require performing an MPI before further flight. However, we do allow the operator
A-010006 thru A-010049 to request a special flight permit to perform the MPI.
A-010075 thru A-010174 x Do not require an entry stating that the ASB has been carried out and no defects were
found.
A-010455 thru A-010460
x Require sending information to the Rotorcraft Certification Office and not to Bell.
A-010581 thru A-010655
Authority for this Rulemaking
A-010742 thru A-010791
Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation
A-010862 thru A-010946 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.
Bell states in ASB 212-10-142 that they have determined that fittings may not have been
manufactured in accordance with the engineering design requirements and may fracture as a result of We are issuing this rulemaking under the authority described in Subtitle VII, Part A,
a non-conformance. They also state that a possibility exists that undetected cracks during the Subpart III, Section 44701, “General requirements.” Under that section, Congress charges the FAA
quenching operation could have occurred at manufacture. 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
FAA’s Determination 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.
We are issuing this EAD because we evaluated all the available information and determined
the unsafe condition described is likely to exist or develop in other products of this same type design. Pursuant to this Authority delegated to me by the Administrator, we are hereby issuing this
Bell is still investigating the cause of these failures and we may issue additional rulemaking to correct Emergency Airworthiness Directive (EAD).
this unsafe condition.
2010-25-51 BELL HELICOPTER TEXTRON, INC.: Directorate Identifier 2010-SW-096-AD.
Effective Date
(a) This EAD is effective upon receipt.
2 3
