Nachrichten für Luftfahrer 2020 Teil 2 (weicht ggf. von Druckversion ab)
(2) For airplanes with a service kit installed in accordance with SEB95-19 or SEB93-5R2: At the
later of the times specified in paragraphs (g)(2)(i) and (ii) of this AD, do a visual inspection of the
lower forward doorpost at the strut attach fitting for cracks in accordance with steps 1.A., 1.B., 1.C.,
and 1.B. (the step following step 1.C.) of the Accomplishment Instructions in SEB95-19; or steps
1.A. and 1.B. of the Accomplishment Instructions in SEB93-5R2; as applicable to your model
airplane. Do not remove the installed service kit; instead, inspect for cracking that extends beyond the
modified parts.
(i) At the applicable time specified in paragraph (g)(1)(i) or (ii) of this AD.
(ii) Within 1,000 hours TIS or 36 calendar months, whichever occurs first, since installing the
service kit.
(h) Repetitive Inspections
(1) If no cracks are found during the initial inspection required by paragraph (g)(1) or (2) of this
AD, thereafter repeat the inspection at intervals not to exceed 36 calendar months or 1,000 hours TIS,
whichever occurs first from the last inspection, as long as no cracks are found.
(2) If cracks are found during any inspection required by paragraph (g)(1) or (h)(1) of this AD,
do the inspection specified in paragraph (g)(2) of this AD within 36 calendar months or 1,000 hours
TIS, whichever occurs first after installing the service kit required by paragraph (i)(1) of this AD.
Thereafter, repeat the inspection at intervals not to exceed 36 calendar months or 1,000 hours TIS,
whichever occurs first from the last inspection, as long as no additional cracks are found.
(i) Corrective Actions
(1) If cracks are found during any inspection required by paragraph (g)(1) or paragraph (h)(1) of
this AD, before further flight, install a service kit in accordance with step 1.D. of the
Accomplishment Instructions in SEB95-19; or step 1.C. of the Accomplishment Instructions in
SEB93-5R2; as applicable to your model airplane.
(2) If cracks are found during any inspection required by paragraph (g)(2) or (h)(2) of this AD,
before further flight, repair the area using a method approved by the Manager, Wichita ACO Branch,
FAA. For a repair method to be approved by the Manager, Wichita ACO Branch as required by this
paragraph, the Manager's approval letter must specifically refer to this AD. You may use the contact
information in paragraph (n)(1) of this AD to obtain FAA approval of your repair method.
(j) Reporting Requirement
Within 30 days after the effective date of this AD, or within 30 days after completing the initial
inspection required by paragraph (g) of this AD, whichever occurs later, report the findings of the
initial inspection (regardless if cracks were found or not) to the FAA at Wichita-COS@faa.gov.
Thereafter, within 30 days after completing each repetitive inspection required by paragraph (h) of
this AD, if any crack was found, report the crack findings to the FAA at Wichita-COS@faa.gov.
Include in your reports the following information:
(1) Name and address of the owner;
(2) Date of the inspection;
(3) Name, address, telephone number, and email address of the person submitting the report;
(4) Airplane serial number and total hours TIS on the airplane at the time of the inspection; and
(5) If any crack was found during the inspection, provide detailed crack information as specified
below:
(i) A sketch or picture detailing the crack location;
(ii) Measured length of the crack(s) found;
(iii) Installation of a Cessna service kit or any other kit or repair before the inspection; and
9
(iv) Installation of any supplemental type certificates (STCs), alterations, repairs, or field
approvals affecting the area of concern or affecting gross weight.
(k) Credit for Previous Actions
(1) You may take credit for the initial inspection required by paragraph (g) of this AD if you
performed the inspection before the effective date of this AD using Cessna Single Engine Service
Bulletin SEB93-5, dated March 26, 1993; or Cessna Single Engine Service Bulletin SEB93-5,
Revision 1, dated September 8, 1995.
(2) You may take credit for the installation required by paragraph (i)(1) of this AD as follows.
(i) For Model 207, T207, 207A, and T207A airplanes with a service kit installed using SK206-
42, SK206-42A, SK206-42B, or SK206-42C: You may take credit for the installation if done before
the effective date of this AD using Cessna Single Engine Service Bulletin SEB93-5, dated March 26,
1993, or Cessna Single Engine Service Bulletin SEB93-5, Revision 1, dated September 8, 1995; if the
reinforcement of the lower forward doorpost bulkhead and wing strut fitting specified in Cessna
Single Engine Service Kit SK207-19A, dated May 29, 2019, is also accomplished within 200 hours
TIS after the effective date of this AD.
(ii) For all other models: You may take credit for the installation if done before the effective date
of this AD using Cessna Single Engine Service Bulletin SEB93-5, dated March 26, 1993; or Cessna
Single Engine Service Bulletin SEB93-5, Revision 1, dated September 8, 1995.
(l) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor
shall a person be subject to a penalty for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that collection of information displays a
current valid OMB Control Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is estimated to be approximately 1 hour
per response, including the time for reviewing instructions, completing and reviewing the collection
of information. All responses to this collection of information are mandatory. Comments concerning
the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at:
800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(m) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Wichita ACO 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 certification office, send it to the attention of the
person identified in paragraph (n)(1) of this AD.
(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.
(n) Related Information
(1) For more information about this AD, contact Bobbie Kroetch, Aerospace Engineer, Wichita
ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4155;
fax: (316) 946-4107; email: bobbie.kroetch@faa.gov or Wichita-COS@faa.gov.
(2) Service information identified in this AD that is not incorporated by reference is available at
the addresses specified in paragraphs (o)(3) and (4) of this AD.
10
(o) 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) Cessna Single Engine Service Bulletin SEB93-5, Revision 2, dated May 29, 2019.
(ii) Cessna Single Engine Service Bulletin SEB95-19, dated December 29, 1995.
(3) For service information identified in this AD, contact Textron Aviation Inc., Textron
Aviation Customer Service, One Cessna Blvd., Wichita, Kansas 67215; telephone: (316) 517-5800;
email: customercare@txtav.com; internet: https://support.cessna.com.
(4) You may view this service information at the FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust, Kansas City, Missouri 64106. For information on the
availability of this material at the FAA, call (816) 329-4148.
(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 fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued on August 24, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification Service.
[FR Doc. 2020-22039 Filed 10-6-20; 8:45 am]
11
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2020-292 38144 Braunschweig
TC AD CF-2020-45 vom 03.11.2020 Fax: +49-531-2355-5298
email: ad@LBA.de
VIKING AIR 13.11.2020
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Viking Air Limited
Hersteller: Viking Air Limited, vormals Bombardier Inc., De Havilland Inc., Boeing of
Canada Ltd. (de Havilland Division), The de Havilland Aircraft Company of
Canada (A Division of Boeing of Canada Ltd.) und The de Havilland Aircraft
Company of Canada, Limited
Muster: DHC-6
Baureihen: DHC-6 Series 1, DHC-6 Series 100, DHC-6 Series 110, DHC-6 Series 200,
DHC-6 Series 210, DHC-6 Series 300, DHC-6 Series 310, DHC-6 Series 320
und DHC-6 Series 400
Werknummern: Alle
Gerätenummer: 2034, EASA.IM.A.575, TC TCDS A-82
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
TC AD CF-2020-45 vom 03.11.2020
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 2020-292 geführt.
Betrifft:
(ATA 27) Flight Controls - Loose Rudder Pedal Torque Tube Quadrant Riveted Connection
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301 5.i) und M.A.303 dür-
fen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genom-
men werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
TC AD CF-2020-45 vom 03.11.2020 herausgegeben oder per Entscheidung Nr. 2019/018/ED übernommen.
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.
D-2020-292 Seite 1 von 1 502/2020
TP 7245E
1 of 2
AD Number: CF-2020-45
AIRWORTHINESS DIRECTIVE
This Airworthiness Directive (AD) is issued pursuant to Canadian Aviation Regulation (CAR) 521.427.
No person shall conduct a take-off or permit a take-off to be conducted in an aircraft that is in their legal
custody and control, unless the requirements of CAR 605.84 pertaining to ADs are met. Standard 625 -
Aircraft Equipment and Maintenance Standards Appendix H provides information concerning alternative
means of compliance (AMOC) with ADs.
Number: Effective Date:
CF-2020-45 17 November 2020
ATA: Type Certificate:
27 A-82
Subject:
Flight Controls – Loose Rudder Pedal Torque Tube Quadrant Riveted Connection
Applicability:
Viking Air Ltd. (formerly de Havilland) model DHC-6 series 1, DHC-6 series 100, DHC-6 series 110,
DHC-6 series 200, DHC-6 series 210, DHC-6 series 300, DHC-6 series 310, DHC-6 series 320 and DHC-
6 series 400 aeroplanes, all serial numbers.
Compliance:
As indicated below, unless already accomplished.
Background:
There have been in-service reports of loose quadrants on the rudder pedal torque tube and signs of loose
rivets or rivet joint wear, such as dark areas or streaks around the rivet heads and quadrant to torque
tube interface. Viking Air Ltd. has determined that inadequate manufacturing tolerances may result in this
condition. This defect, if not detected and corrected, could result in the affected parts deteriorating until
the rivets fail, leading to loss of control of the rudder and possible loss of control of the aeroplane.
To detect and correct this condition, this AD mandates a one-time detailed inspection of the rudder pedal
torque tube quadrant assembly, and rectification, as required, of the affected parts.
Viking Air Ltd. has published Service Bulletin (SB) V6/0067, Revision NC, dated 16 July 2020 (referred to
as “the SB” in this AD), providing Accomplishment Instructions for the one-time detailed inspection for
looseness of the affected parts.
Corrective Actions:
A. Within three months from the effective date of this AD, inspect the rudder pedal torque tube quadrant
assembly riveted connection in accordance with the Accomplishment Instructions of the SB.
B. If any looseness of the rudder pedal torque tube quadrant assembly or loose rivets or rivet joint
wear/smoking rivets is detected, as defined in the SB, before further flight, repair or replace the
affected parts in accordance with the Accomplishment Instructions of the SB.
The use of later revisions of the SB that are approved by the Chief, Continuing Airworthiness, Transport
Canada, is acceptable for compliance to the requirements of this AD.
CF-2020-45 2 of 2 Authorization: For the Minister of Transport, ORIGINAL SIGNED BY Rémy Knoerr Chief, Continuing Airworthiness Issued on 3 November 2020 Contact: Audrey Vézina-Manzo, Continuing Airworthiness, Ottawa, telephone 888-663-3639, facsimile 613-996-9178 or e-mail AD-CN@tc.gc.ca or any Transport Canada Centre.
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2020-293 38144 Braunschweig
EASA AD 2020-0247 vom 10.11.2020 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS HELICOPTERS 13.11.2020
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: AIRBUS HELICOPTERS
Hersteller: Airbus Helicopters, vormals Eurocopter, Eurocopter France
Muster: EC 120
Baureihen: EC 120 B
Werknummern: Alle
Gerätenummer: 3065, EASA.R.508
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2020-0247 vom 10.11.2020
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 2020-293 geführt.
Betrifft:
(ATA 32) Landing Gear - Skid Tubes - Inspection .
(RFM) Rotorcraft Flight Manual - Section Limitations - Amendment
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301 5.i) und M.A.303 dür-
fen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genom-
men werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2020-0247 vom 10.11.2020 herausgegeben oder per Entscheidung Nr. 2019/018/ED übernommen.
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.
D-2020-293 Seite 1 von 1 513/2020
EASA AD No.: 2020-0247
Airworthiness Directive
AD No.: 2020-0247
Issued: 10 November 2020
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: Type/Model designation(s):
AIRBUS HELICOPTERS EC 120 B helicopters
Effective Date: 17 November 2020
TCDS Number(s): EASA.R.508
Foreign AD: Not applicable
Supersedure: None
ATA 32 – Landing Gear – Skid Tubes – Inspection
ATA – Rotorcraft Flight Manual – Section Limitations – Amendment
Manufacturer(s):
Airbus Helicopters (AH), formerly Eurocopter, Eurocopter France
Applicability:
EC 120 B helicopters, all serial numbers (s/n).
Definitions:
For the purpose of this AD, the following definitions apply:
Autorotation landing: Power-off landing with touchdown completed.
Affected part: Left-hand (LH) and right-.hand (RH) skid tubes, having Part Number (P/N)
C321A2107101 (LH), P/N C321A2108101 (RH), P/N C321A2107102 (LH), P/N C321A2108102 (RH),
P/N C321A2502102 (LH), or P/N C321A2503102 (RH), installed on landing gear having P/N
C321A2101053, P/N C321A2101054, P/N C321A2501051 or P/N C321A2601053.
Serviceable part: A landing gear skid tube which is not an affected part; or an affected part having
accumulated less than 1 450 autorotation landings since its first installation on a helicopter; or an
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EASA AD No.: 2020-0247
affected part having accumulated less than 1 450 autorotation landings since last accomplishment
of the corrective action(s) as required by paragraph (4) of this AD.
The ASB: AH EC120 Emergency Alert Service Bulletin (ASB) 05A022.
Groups: Group 1 are helicopters having s/n 1482, 1568, 1573, 1596, 1600, 1601, 1605, 1606, 1609,
1610, 1611, 1612, 1613, 1615, 1616, 1617, 1620, 1622, 1623, 1624, 1625, 1626, 1628, 1630, 1631,
1635, 1637, 1638, 1641, 1643, 1645, 1646, 1647, 1648, 1649 or 1650. Group 2 helicopters are all
other s/n.
Reason:
Cracks have been reportedly found on landing gear skid of a helicopter with a high number of
autorotation landings. Similar cracks have been found on other helicopters, also having
accumulated a high number of autorotation landings.
This condition, if not detected and corrected, could lead to failure of the landing gear skid, possibly
resulting in rollover of the helicopter after a hard landing and consequent injury to occupants.
To address this potential unsafe condition, AH published the ASB to provide inspection instructions
of the affected parts, and to define a temporary weight limitation until these inspections are
implemented.
For the reason described above, this AD requires amendment of the applicable Rotorcraft Flight
Manual (RFM), repetitive inspections of the affected parts and, depending on findings,
accomplishment of applicable corrective action(s).
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
RFM Amendment:
(1) For Group 1 helicopters: Before an affected part exceeds 1 450 autorotation landings since first
installation on a helicopter (see Note 1 of this AD), or before next flight after the effective date
of this AD, whichever occurs later, amend the applicable RFM in accordance with the
instructions of paragraph 1.E of the ASB, inform all flight crews and, thereafter, operate the
helicopter accordingly.
Note 1: For the purpose of this AD, if the number of autorotation landings of an affected part is
unknown, it must be assumed to be above 1 450.
Repetitive Inspections:
(2) For Group 1 helicopters: Before an affected part exceeds 1 450 autorotation landings since first
installation on a helicopter (see Note 1 of this AD), or before next flight after the effective date
of this AD, whichever occurs later, and, thereafter, before each first flight of the day,
accomplish an external visual inspection of that affected part in accordance with the
instructions of paragraph 3.B.2 of the ASB.
TE.CAP.00110-010 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 4
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EASA AD No.: 2020-0247
(3) For Group 1 helicopters: Before an affected part exceeds 1 400 autorotation landings since its
first installation on a helicopter (see Note 1 of this AD), or within 3 months after the effective
date of this AD, whichever occurs later, and, thereafter, at intervals not exceeding 13
autorotation landings, accomplish an internal borescope inspection of that affected part in
accordance with the instructions of paragraph 3.B.2 of the ASB.
Corrective Action(s):
(4) If, during any inspection as required by paragraph (2) or (3) of this AD, as applicable,
discrepancies are detected, as defined in the ASB, before next flight, contact AH for approved
repair instructions and, within the compliance time specified therein, accomplish those
instructions accordingly.
(5) Replacing each affected part on a helicopter with a serviceable part is an acceptable alternative
method to comply with the requirements of paragraph (4) of this AD for that helicopter.
RFM Amendment Removal:
(6) After accomplishment of the initial internal borescope inspection of affected parts on a
helicopter, as required by paragraph (3) of this AD, remove the RFM amendment, previously
inserted as required by paragraph (1) of this AD, from the RFM of that helicopter. After
amendment of the RFM, inform all flight crews and operate the helicopter accordingly.
Terminating Action:
(7) Accomplishment of the initial internal borescope inspection of all affected parts on a helicopter,
as required by paragraph (3) of this AD, constitutes terminating action for the external visual
inspections as required by paragraph (2) of this AD for that helicopter.
Parts Installation:
(8) For Group 1 and Group 2 helicopters: From the effective date of this AD, it is allowed to install
on any helicopter an affected part, provided it is a serviceable part, as defined in this AD, and
that, following installation, it is inspected as required by this AD.
Ref. Publications:
AH EC120 Emergency ASB 05A022 original issue dated 20 October 2020.
The use of later approved revisions of the above-mentioned document is acceptable for compliance
with the requirements of this AD.
Remarks:
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of
Compliance for this AD.
2. Based on the required actions and the compliance time, EASA have decided to issue a Final AD
with Request for Comments, postponing the public consultation process until after publication.
3. Enquiries regarding this AD should be referred to the EASA Programming and Continued
Airworthiness Information Section, Certification Directorate. E-mail: ADs@easa.europa.eu.
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