Nachrichten für Luftfahrer 2021 Teil 2 (weicht ggf. von Druckversion ab)
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Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by searching for and locating
Docket No. FAA-2021-0661; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays. The AD docket contains this final rule, any comments
received, and other information. The address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Nicholas Paine, Aviation Safety Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238-7116; fax: (781) 238-
7199; email: nicholas.j.paine@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to
supersede AD 2011-07-02, Amendment 39-16639 (76 FR 16526, March 24, 2011), (AD 2011-07-
02). AD 2011-07-02 applied to all P&W JT8D-209, JT8D-217, JT8D-217A, JT8D-217C, and JT8D-
219 model turbofan engines. The NPRM published in the Federal Register on August 27, 2021 (86
FR 48080). The NPRM was prompted by a report of an MD-82 airplane, equipped with JT8D-217C
model turbofan engines that, on approach to Taipei Songshan Airport, experienced an engine surge
on the number one engine resulting in LPT blade fracture and uncontained LPT blade failure. An
inspection by the manufacturer determined that this event was caused by shroud notch wear of the
LPT blades, which led to changes in the vibration mode and subsequent high-cycle fatigue of the
airfoil. In addition to this event, the FAA received reports of five events that involved uncontained
failure of the LPT blades on the affected engines. Based on its investigation of these events, P&W
determined that revised or more restrictive inspection thresholds and replacement intervals of the 3rd-
stage and 4th-stage LPT blades are necessary and revised its service information accordingly. In the
NPRM, the FAA proposed to require an initial torque inspection of certain 3rd-stage LPT blades and
repetitive torque inspections of 4th-stage LPT blades for shroud notch wear at revised inspection
thresholds and intervals. In the NPRM, the FAA also proposed to require replacement of the 3rd-
stage and 4th-stage LPT blades before accumulating 5,000 hours time-in-service.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from one commenter. The Boeing Company supported the NPRM
without change.
Conclusion
The FAA reviewed the relevant data, considered the comment received, and determined that air
safety requires adopting the AD as proposed. Accordingly, the FAA is issuing this AD to address the
unsafe condition on these products. This AD is adopted as proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
21.12.2021
The FAA reviewed Pratt & Whitney Alert Service Bulletin (ASB) No. JT8D A6224, Revision
No. 7, dated August 26, 2019. This service information specifies procedures for the initial and
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repetitive torque inspections of the 3rd-stage and 4th-stage LPT blades for shroud notch wear at
revised inspection thresholds and intervals. This service information is reasonably available because
the interested parties have access to it through their normal course of business or by the means
identified in ADDRESSES.
Other Related Service Information
The FAA reviewed Pratt & Whitney ASB No. JT8D A6494, Revision No. 1, dated January 26,
2010, Pratt & Whitney ASB JT8D A6507, dated November 2, 2020, and Sections 72-53-12 through
72-53-13 of Pratt & Whitney Engine Maintenance Manual (EMM), Part No. 773128, Revision 107,
dated October 15, 2020. Pratt & Whitney ASB No. JT8D A6494, Revision No. 1, dated January 26,
2010, describes procedures for replacing the LPT-to-exhaust case bolts and nuts and installing the
crushable sleeve spacers. Pratt & Whitney ASB JT8D A6507, dated November 2, 2020, describes
procedures for replacing the 3rd-stage and 4th-stage LPT blades. Sections 72-53-12 through 72-53-13
of Pratt & Whitney EMM, Part No. 773128, Revision 107, dated October 15, 2020, describe
procedures for inspecting and repairing the 3rd-stage and 4th-stage LPT blades.
Costs of Compliance
The FAA estimates that this AD affects 42 engines installed on airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
Action Labor cost Parts Cost per Cost on U.S.
cost product operators
Inspect 3rd-stage and 4th-stage LPT 1 work-hour × $85 $0 $85 $3,570
blades per hour = $85
Replace 3rd-stage and 4th-stage 150 work-hours × $350,000 $362,750 $15,235,500
LPT blades $85 per hour =
$12,750
Replace the LPT-to-exhaust case 1.5 work-hours × $4,576 $4,703.50 $197,547
bolts and nuts and install the $85 per hour =
crushable sleeve spacers 127.50
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.
The FAA is 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.
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Regulatory Findings
The FAA has 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 this AD:
(1) Is not a “significant regulatory action” under Executive Order 12866,
(2) Will not affect intrastate aviation in Alaska, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR
part 39 as follows:
PART 39–AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13 [Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive AD 2011-07-02, Amendment 39-16639 (76 FR 16526, March
24, 2011); and
b. Adding the following new airworthiness directive:
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AIRWORTHINESS
FAA DIRECTIVE
Aviation Safety
www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html
2021-22-19 Pratt & Whitney: Amendment 39-21792; Docket No. FAA-2021-0661; Project
Identifier AD-2020-01349-E.
(a) Effective Date
This airworthiness directive (AD) is effective December 28, 2021.
(b) Affected ADs
This AD replaces AD 2011-07-02, Amendment 39-16639 (76 FR 16526, March 24, 2011).
(c) Applicability
This AD applies to Pratt & Whitney (P&W) JT8D-209, JT8D-217, JT8D-217A, JT8D-217C, and
JT8D-219 model turbofan engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section.
(e) Unsafe Condition
This AD was prompted by a report of an MD-82 airplane, equipped with a JT8D-217C model
turbofan engine, experiencing an engine surge that resulted in the fracture of the low-pressure turbine
(LPT) blade and uncontained release of the LPT blade. Five prior uncontained LPT blade failures
were also reported on affected model turbofan engines. The FAA is issuing this AD to prevent LPT
blade fracture and uncontained release of the LPT blade. The unsafe condition, if not addressed,
could result in uncontained engine debris, damage to the engine, and damage to the aircraft.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Required Actions
(1) For JT8D-209, JT8D-217, and JT8D-217A model turbofan engines, within the compliance
times specified in the Accomplishment Instructions, Part 1: JT8D-209, -217, -217A Engines (Part 1),
paragraph 1.A., of P&W Alert Service Bulletin No. JT8D A6224, Revision No. 7, dated August 26,
2019 (the ASB), perform an initial torque inspection for shroud notch wear of the 3rd-stage LPT
blades using the procedures in Part 1, paragraph 1, of the ASB.
(i) Thereafter, within the applicable reinspection interval specified in Table 1–Reinspection
Interval for all 3rd Stage Blades, of the ASB, repeat the torque inspection for shroud notch wear
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required by paragraph (g)(1) of this AD.
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(ii) If the results of the torque inspection required by paragraphs (g)(1) or (g)(1)(i) of this AD
meet the criteria for engine removal specified in Table 1–Reinspection Interval for all 3rd Stage
Blades, of the ASB, perform piece-part inspections in accordance with the Instructions for Continued
Airworthiness (ICA) on all 3rd-stage LPT blades before exceeding 20 hours time-in-service (TIS)
since the last torque inspection.
(2) For JT8D-209, JT8D-217, and JT8D-217A model turbofan engines, within the compliance
times specified in Table A or Table B, of the ASB, as applicable, perform an initial torque inspection
for shroud notch wear of the 4th-stage LPT blades using the procedures in Part 1, paragraph 1, of the
ASB. Wherever the ASB refers to “Revision 7 Release Date” and “At SB Release Date,” use the
effective date of this AD.
(i) For engines in which the last inspection prior to the effective date of this AD had a torque
inspection result of less than 15 LB-IN on any 4th-stage LPT blade, perform piece-part inspections in
accordance with the ICA on all 3rd-stage and 4th-stage LPT blades within 20 hours TIS after the
effective date of this AD.
(ii) Thereafter, within the applicable reinspection interval specified in Table 2–Reinspection
Interval for all 4th Stage Blades, of the ASB, repeat the torque inspection for shroud notch wear
required by paragraph (g)(2) of this AD.
(iii) If the results of the torque inspection required by paragraphs (g)(2) or (g)(2)(ii) of this AD
meet the criteria for engine removal specified in Table 2–Reinspection Interval for all 4th Stage
Blades, of the ASB, perform piece-part inspections in accordance with the ICA on all 3rd-stage and
4th-stage LPT blades before exceeding 20 hours TIS since the last torque inspection.
(3) For JT8D-217C and JT8D-219 model turbofan engines, within the compliance times
specified in Table A or Table B, of the ASB, as applicable, perform an initial torque inspection for
shroud notch wear of the 4th-stage LPT blades using the procedures in the Accomplishment
Instructions, Part 2: JT8D-217C, -219 Engines (Part 2), paragraph 1, of the ASB. Wherever the ASB
refers to “Revision 7 Release Date” and “At SB Release Date,” use the effective date of this AD.
(i) For engines in which the last inspection prior to the effective date of this AD had a torque
inspection result of less than 15 LB-IN on any 4th-stage LPT blade, perform piece-part inspections in
accordance with the ICA on all 3rd-stage and 4th-stage LPT blades within 20 hours TIS after the
effective date of this AD.
(ii) Thereafter, within the reinspection interval specified in Table 3–Reinspection Interval for all
4th Stage Blades, of the ASB, repeat the torque inspection for shroud notch wear required by
paragraph (g)(3) of this AD.
(iii) If the results of the torque inspection required by paragraph (g)(3) and (g)(3)(ii) of this AD
meet the criteria for engine removal specified in Table 3–Reinspection Interval for all 4th Stage
Blades, of the ASB, perform piece-part inspections in accordance with the ICA on all 3rd-stage and
4th-stage LPT blades before exceeding 20 hours TIS since the last torque inspection.
(4) At the first engine shop visit after January 1, 2023, or prior to accumulating 5,000 TIS on the
3rd-stage and 4th-stage LPT blades, whichever occurs later, but not to exceed 6 years after the
effective date of the AD, replace the 3rd-stage and 4th-stage LPT blades with parts eligible for
installation.
(5) Thereafter, prior to accumulating 5,000 hours TIS on the 3rd-stage and 4th-stage LPT blades
since their last replacement, replace the 3rd-stage and 4th-stage LPT blades with parts eligible for
installation.
(6) After every replacement of the 3rd-stage or 4th-stage LPT blades, perform initial and
repetitive torque inspections of the 3rd-stage or 4th-stage LPT blades using, as applicable, the
accomplishment instructions and compliance times in Part 1, paragraph 1, or Part 2, paragraph 1, of
the ASB.
(i) If the results of the torque inspection required by paragraph (g)(6) of this AD meet the criteria
for engine removal specified in Table 1, 2 or 3, of the ASB, as applicable, perform piece-part
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inspections in accordance with the ICA on all 3rd-stage and 4th-stage LPT blades before exceeding
20 hours TIS since the last torque inspection.
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(ii) [Reserved]
(7) The initial inspection or the reinspection interval should not be reset unless the blades are
refurbished. Whenever a used blade is reinstalled in a rotor, the previous used time should be
subtracted from the initial inspection threshold.
(8) Whenever a refurbished or used blade is intermixed with zero hours time-since-new (TSN)
blades in a rotor, use the lowest initial inspection threshold that is applicable.
(9) At the next accessibility to the LPT-to-exhaust case bolts and nuts after the effective date of
this AD, do the following:
(i) Replace the bolts with part number (P/N) MS9557-26 bolts;
(ii) Replace the nuts with P/N 375095 nuts or P/N 490270 nuts; and
(iii) Install crushable sleeve spacers, P/N 822903, under the head of the bolts.
Note 1 to paragraph (g): Guidance on replacing the 3rd-stage and 4th-stage LPT blades can be
found in P&W ASB JT8D A6507, dated November 2, 2020.
Note 2 to paragraph (g): Guidance on replacing the LPT-to-exhaust case bolts and nuts and
installing the crushable sleeve spacers can be found in P&W ASB No. JT8D A6494, Revision No. 1,
dated January 26, 2010.
(h) Definitions
For the purpose of this AD:
(1) An “engine shop visit” is the induction of an engine into the shop for maintenance involving
the separation of pairs of major mating engine flanges, except that the separation of engine flanges
solely for the purposes of transportation without subsequent engine maintenance does not constitute
an engine shop visit.
(2) Accessibility to the LPT-to-exhaust case bolts refers to maintenance involving the inner
turbine fan ducts being removed from the engine.
(3) Parts eligible for installation are 3rd-stage or 4th-stage LPT blades with less than 5,000 hours
TIS.
(4) A “piece-part inspection” is when the blades are removed from the rotor.
(5) A “used blade” refers to a 3rd-stage or 4th-stage LPT blade that has more than zero hours
TSN.
(i) Credit for Previous Actions
You may take credit for any initial torque inspection for shroud notch wear required by
paragraphs (g)(1) through (3) of this AD if you performed the initial inspection before the effective
date of this AD using P&W ASB No. JT8D A6224, Revision No. 5, dated June 11, 2004, or Revision
No. 6, dated May 3, 2007.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your
request to your principal inspector or local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ECO Branch, send it to the attention of the person
identified in paragraph (k) of this AD. You may email your request to: ANE-AD-AMOC@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a
principal inspector, the manager of the local flight standards district office/certificate holding district
office.
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(k) Related Information
For more information about this AD, contact Nicholas Paine, Aviation Safety Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238-7116; fax: (781) 238-
7199; email: nicholas.j.paine@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the
service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD,
unless the AD specifies otherwise.
(i) Pratt & Whitney Alert Service Bulletin No. JT8D A6224, Revision No. 7, dated August 26,
2019.
(ii) [Reserved]
(3) For service information identified in this AD, contact Pratt & Whitney, 400 Main Street, East
Hartford, CT 06118; phone: (800) 565-0140; email: help24@prattwhitney.com; website:
https://fleetcare.prattwhitney.com.
(4) You may view this service information at FAA, Airworthiness Products Section, Operational
Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of
this material at the FAA, call (781) 238-7759.
(5) You may view this service information that is incorporated by reference at the National
Archives and Records Administration (NARA). For information on the availability of this material at
NARA, email: fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued on October 21, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification Service.
[FR Doc. 2021-25500 Filed 11-22-21; 8:45 am]
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T12 -
D-2013-079R14 38144 Braunschweig
EASA AD 2015-0226R6 vom 08.12.2021 Fax: +49-531-2355-5197
email: AD@LBA.de
GOODRICH HOIST 10.12.2021
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: Leonardo S.p.A.,
Bell Textron, Inc.,
Bell Textron Canada Ltd.,
Airbus Helicopters,
Airbus Helicopters Deutschland GmbH,
MD Helicopters, Inc.,
Sikorsky Aircraft Corporation
Hersteller: Leonardo S.p.A. Helicopter Division (vormals Finmeccanica S.p.A. Helicopter
Division, AgustaWestland S.p.A., Agusta S.p.A. und Costruzioni Aeronautiche
Giovanni Agusta), Bell Textron, Inc. (vormals Bell Helicopter Textron, Inc.), Bell
Textron Canada Ltd., vormals Bell Helicopter Textron Canada, Airbus
Helicopters (vormals Eurocopter, Eurocopter France und Aerospatiale), Airbus
Helicopters Deutschland GmbH (vormals Eurocopter Deutschland GmbH),
Airbus Helicopters Inc. (vormals American Eurocopter LLC), MD Helicopters,
Inc. (vormals McDonnell Douglas Helicopter Systems) und Sikorsky Aircraft
Corporation
Muster: Leonardo S.p.A.:
AW109SP
AB139 / AW139
AB412
Bell Textron, Inc. (BTI):
Bell 212
Bell 214
Bell 412
STC SH3189SO
Bell Textron Canada Ltd. (BTCL):
Bell 429
Bell 430
Airbus Helicopters (AH):
AS 365 N3
AS 332 L2
EC 225 LP
Airbus Helicopters Deutschland GmbH (AHD):
MBB-BK117 C-2
EC135
EC635
MD Helicopters (MDHI):
MD900
Sikorsky Aircraft Corporation:
S-61
S-76
S-92A
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Baureihen: Leonardo AW109SP, AB139, AW139 und AB412 (alle Baureihen). BTI 212, 214
und 412 (alle Baureihen). BTCL 429 und 430. Airbus Helicopters AS 365 N3,
AS 332 L2 und EC225 LP. Airbus Helicopters Deutschland MBB-BK117 C-2,
EC135 und EC635 (alle Baureihen). MD Helicopters MD900. Sikorsky S-61
(alle Baureihen), S-76A, S-76B, S-76C und S-92A.
Werknummern: Alle
Betroffen sind Hubschrauber mit einer Goodrich Außenwinde/Rettungswinde
(Hoist), die in der Tabelle 1 der EASA AD 2015-0226R6 (Table 1 - Affected
Goodrich Hoists P/N) aufgeführt ist.
Gerätenummer: 3039, 3045, 3047, 3049, 3050, 3054, 3061, 3064, 3066, EASA.R.002,
EASA.R.005, EASA.R.006, EASA.R.009, EASA.R.010, EASA.R.105,
EASA.R.114, EASA.IM.R.001, EASA.IM.R.106, EASA.IM.R.113,
EASA.IM.R.114, EASA.IM.R.506, FAA TCDS 1H15, H1NE, H4SW, H6SW,
H19NM und R00024BO, TC TCDS H-88 und H-107, FAA STC SH3189SO
Revisionsstand:
Diese LTA ersetzt D-2013-079R13 vom 13.08.2020
Airworthiness Directive der ausländischen Behörde:
EASA AD 2015-0226R6 vom 08.12.2021
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 2019/018/ED übernommen und sind somit ebenfalls Airworthin-
ess Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2013-079R14 geführt.
Betrifft:
(ATA 25) Equipment / Furnishings - Hoist - Test / Replacement
Hinweis: Die EASA AD ersetzt die Maßnahmen der FAA AD 2013-06-51 (NOT ADOPTED / LTA D-2013-104R2).
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301(f)(1), ML.A.301(d)(1),
M.A.303 und ML.A.303 dürfen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen
Termin nur in Betrieb genommen werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchge-
führt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2015-0226R6 vom 08.12.2021 herausgegeben oder per Entscheidung Nr. 2019/018/ED übernom-
men.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsanweisun-
gen direkt in der Bundesrepublik Deutschland gültig und bedürfen keiner Umsetzung durch das Luftfahrt-
Bundesamt.
Mit Hilfe dieser Übersichtsseite veröffentlicht das Luftfahrt-Bundesamt ebenfalls die über § 14 Abs. 2 direkt
gültigen Lufttüchtigkeitsanweisungen der EASA in den Nachrichten für Luftfahrer und im Internet unter
www2.LBA.de/LTAs/. Dieser Service dient reinen Informationszwecken und liegt keinem Verwaltungsver-
fahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
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EASA AD No.: 2015-0226R6
Airworthiness Directive
AD No.: 2015-0226R6
Issued: 08 December 2021
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EU) 2018/1139 on behalf of the European Union, its Member States and of the European third
countries that participate in the activities of EASA under Article 129 of that Regulation.
This AD is issued in accordance with Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 Annex I, Part M.A.301, the
continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which
an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [Regulation (EU) 1321/2014 Annex I,
Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (EU) 2018/1139, Article 71 exemption].
Design Approval Holder’s Name: Helicopter Type/Model designation(s):
LEONARDO S.p.A. AW109SP, AB/AW 139 and AB412
BELL TEXTRON, Inc. 212, 214 and 412, and STC SH3189SO
BELL TEXTRON CANADA Ltd. 429 and 430
AIRBUS HELICOPTERS AS 365 N3, AS 332 L2 and EC225 LP
AIRBUS HELICOPTERS DEUTSCHLAND GmbH MBB-BK 117 C-2, EC135 and EC635
MD HELICOPTERS, Inc. MD900
SIKORSKY AIRCRAFT CORPORATION S-61, S-76 and S-92A
Effective Date: Revision 6: 15 December 2021
Revision 5: 30 July 2020
Revision 4: 11 June 2019
Revision 3: 01 June 2016
Revision 2: 15 March 2016
Original issue and Revision 1: 21 November 2015
TCDS Number(s): EASA.IM.R.001, EASA.R.002, EASA.R.005, EASA.R.006, EASA.R.009, EASA.R.105,
EASA.IM.R.113, EASA.R.510 and EASA.IM.R.506; USA 1H15, H19NM, H4SW and
H6SW; Canada H-88; and Italy A 157.
Foreign AD: This AD is related to FAA AD 2013-06-51 dated 28 June 2013, and to Transport
Canada AD CF-2017-23 dated 21 July 2017.
Revision: This AD revises EASA AD 2015-0226R5 dated 23 July 2020. The original issue of
this AD superseded EASA AD 2015-0160 dated 04 August 2015.
ATA 25 – Equipment / Furnishings – Hoist – Test / Replacement
Manufacturer(s):
Leonardo S.p.A Helicopter Division, formerly Finmeccanica S.p.A. Helicopter Division,
AgustaWestland S.p.A.; Agusta S.p.A.; Costruzioni Aeronautiche Giovanni Agusta, Bell Textron Inc.
(BTI), formerly Bell Helicopter Textron, Inc.; Bell Textron Canada Ltd (BTCL), formerly Bell Helicopter
21.12.2021
TE.CAP.00110-010 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 10
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
