Nachrichten für Luftfahrer 2017 Teil 2 (weicht ggf. von Druckversion ab)
(1) Is not a “significant regulatory action” under Executive Order 12866,
(2) Is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979),
(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
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.
Adoption of 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 adding the following new airworthiness directive (AD):
4
AIRWORTHINESS
FAA DIRECTIVE
Aviation Safety
www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html
2017-23-07 The Boeing Company: Amendment 39-19101; Docket No. FAA-2017-0773; Product
Identifier 2017-NM-067-AD.
(a) Effective Date
This AD is effective December 26, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -
500 series airplanes, certificated in any category.
(2) Installation of Supplemental Type Certificate (STC) ST01219SE
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ebd1cec7b301293e86257cb300455
57a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD.
Therefore, for airplanes on which STC ST01219SE is installed, a “change in product” alternative
method of compliance (AMOC) approval request is not necessary to comply with the requirements of
14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by the report of a crack indication in the horizontal flange of the lower
chord of the left wing rear spar at wing buttock line (WBL) 157 and multiple reports of similar crack
findings on other airplanes. We are issuing this AD to detect and correct cracking of the lower chord
of the rear spar and the lower aft skin at WBL 157. Undetected cracks could lead to the inability of
the lower chord of the rear spar, a principal structural element, to sustain limit load, which could
adversely affect the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Required Actions
(1) For Group 2 airplanes identified in Boeing Alert Service Bulletin 737-57A1333, dated May
12, 2017: Except as required by paragraph (h) of this AD, at the applicable times specified in
paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-57A1333, dated May 12, 2017,
5
do all applicable actions identified as “RC” (required for compliance) in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-57A1333, dated May 12, 2017.
(2) For Group 1 airplanes identified in Boeing Alert Service Bulletin 737-57A1333, dated May
12, 2017: Within 120 days after the effective date of this AD, inspect the airplane and do all
applicable corrective actions using a method approved in accordance with the procedures specified in
paragraph (i) of this AD.
(h) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 737-57A1333, dated May 12, 2017, uses the phrase
“after the original issue date of this service bulletin,” for purposes of determining compliance with
the requirements of this AD, the phrase “after the effective date of this AD” must be used.
(2) Where Boeing Alert Service Bulletin 737-57A1333, dated May 12, 2017, specifies contacting
Boeing, and specifies that action as RC: This AD requires using a method approved in accordance
with the procedures specified in paragraph (i) of this AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles 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 (j) of this AD. Information may be emailed to: 9-ANM-LAACO-
AMOC-Requests@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.
(3) An AMOC that provides an acceptable level of safety may be used for any repair,
modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes
Organization Designation Authorization (ODA) that has been authorized by the Manager, Los
Angeles ACO Branch, to make those findings. To be approved, the repair method, modification
deviation, or alteration deviation must meet the certification basis of the airplane, and the approval
must specifically refer to this AD.
(4) Except as required by paragraph (h)(2) of this AD: For service information that contains steps
that are labeled as RC, the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply.
(i) The steps labeled as RC, including substeps under an RC step and any figures identified in an
RC step, must be done to comply with the AD. If a step or substep is labeled “RC Exempt,” then the
RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC
steps, including substeps and identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with
the operator's maintenance or inspection program without obtaining approval of an AMOC, provided
the RC steps, including substeps and identified figures, can still be done as specified, and the airplane
can be put back in an airworthy condition.
(j) Related Information
For more information about this AD, contact Payman Soltani, Aerospace Engineer, Airframe
Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5313; fax: 562-627-5210; email: payman.soltani@faa.gov.
6
(k) 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) Boeing Alert Service Bulletin 737-57A1333, dated May 12, 2017.
(ii) Reserved.
(3) For service information identified in this AD, contact Boeing Commercial Airplanes,
Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal
Beach, CA 90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com.
(4) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-
227-1221.
(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, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on November 6, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
7
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2017-290 38144 Braunschweig
TC AD CF-2017-35 vom 29.11.2017 Fax: +49-531-2355-5298
email: ad@LBA.de
BOMBARDIER 05.12.2017
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Bombardier Inc.
Hersteller: Bombardier Inc.
Muster: DHC-8
Baureihen: DHC-8-400, DHC-8-401 und DHC-8-402
Werknummern: 4001 und folgende
Gerätenummer: 2868, EASA.IM.A.191, TC TCDS A-142
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
TC AD CF-2017-35 vom 29.11.2017
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 02/2003 übernommen und sind somit ebenfalls Airworthiness
Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2017-290 geführt.
Betrifft:
(ATA 27) Flight Controls - Power Lever Module - Introduction of Operational Check of Ground Spoiler Switches
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen Luftfahr-
zeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen werden,
wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
TC AD CF-2017-35 vom 29.11.2017 herausgegeben oder per Entscheidung Nr. 02/2003 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-2017-290 Seite 1 von 1 517/2017
TP 7245E
1 of 1
AD Number: CF-2017-35
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) to ADs.
Number: Effective Date:
CF-2017-35 13 December 2017
ATA: Type Certificate:
27 A-142
Subject:
Flight Controls - Power Lever Module – Introduction of Operational Check of Ground Spoiler Switches.
Applicability:
Bombardier Inc. model DHC-8-400, -401 and -402 aeroplanes, serial numbers 4001 and subsequent.
Compliance:
As indicated below, unless already accomplished.
Background:
There has been an incident of uncommanded deployment of the ground spoilers when the power levers
were advanced for take-off. The warning horn sounded and the pilot rejected the take-off. The
subsequent investigation determined the root cause of the spoiler deployment was faulty switches in the
power lever module. An uncommanded deployment of the ground spoilers may lead to a runway
excursion.
This AD mandates the incorporation of a new Certification Maintenance Requirement (CMR) task to
check the ground spoiler switches in the power lever module.
Corrective Actions:
A. Within 30 days from the effective date of this AD, revise the Transport Canada approved
maintenance schedule to incorporate CMR Task 276000-110 Operational Check of the Ground
Spoiler Switches in the Power Lever Module, as introduced by Temporary Revision (TR) ALI-0173
dated 14 March 2017, of the DHC-8-400 Maintenance Requirements Manual (MRM), PSM 1-84-7.
Compliance with superseding TR or later revisions of the MRM also meets the requirements of this
paragraph.
B. Within 8000 hours air time from the effective date of this AD, accomplish CMR Task 276000-110.
Thereafter, follow the task interval specified in the DHC-8-400 MRM, PSM 1-84-7 TR ALI-0173, dated
14 March 2017, or later revisions of this task approved by Transport Canada.
Authorization:
For the Minister of Transport,
ORIGINAL SIGNED BY
Rémy Knoerr
Chief, Continuing Airworthiness
Issued on 29 November 2017
Contact:
Brian Daly, Continuing Airworthiness, Ottawa, telephone 1-888-663-3639, facsimile 613-996-9178 or
e-mail AD-CN@tc.gc.ca or any Transport Canada Centre.
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2017-291 38144 Braunschweig
EASA AD 2017-0239 vom 30.11.2017 Fax: +49-531-2355-5298
email: ad@LBA.de
DORNIER 05.12.2017
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: 328 Support Services GmbH
Hersteller: Dornier Luftfahrt GmbH, Fairchild Dornier GmbH, AvCraft Aerospace GmbH
Muster: Dornier 328
Baureihen: Dornier 328-100 und Dornier 328-300
Werknummern: Alle
Gerätenummer: 2534, EASA.A.096
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2017-0239 vom 30.11.2017
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 02/2003 übernommen und sind somit ebenfalls Airworthiness
Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2017-291 geführt.
Betrifft:
(ATA 55) Stabilizers - Horizontal Stabilizer Rear Bearing Supports - Inspection / Replacement / Rear Spar
Modification
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen Luftfahr-
zeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen werden,
wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2017-0239 vom 30.11.2017 herausgegeben oder per Entscheidung Nr. 02/2003 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-2017-291 Seite 1 von 1 518/2017
EASA AD No.: 2017-0239
Airworthiness Directive
AD No.: 2017-0239
Issued: 30 November 2017
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EC) 216/2008 on behalf of the European Union, its Member States and of the European third
countries that participate in the activities of EASA under Article 66 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 (EC) 216/2008, Article 14(4) exemption].
Design Approval Holder’s Name: Type/Model designation(s):
328 SUPPORT SERVICES GmbH Dornier 328 aeroplanes
Effective Date: 14 December 2017
TCDS Number(s): EASA.A.096
Foreign AD: Not Applicable
Supersedure: None
ATA 55 – Stabilizers – Horizontal Stabilizer Rear Bearing Supports – Inspection /
Replacement / Rear Spar Modification
Manufacturer(s):
Dornier Luftfahrt GmbH, Fairchild-Dornier GmbH, AvCraft Aerospace GmbH
Applicability:
Dornier 328-100 aeroplanes, all serial numbers (s/n), and
Dornier 328-300 aeroplanes, all s/n.
Reason:
Occurrences were reported on horizontal stabilizer bearing supports being found corroded at the
contact surface to the horizontal stabilizer rear spar. The corroded area was at the lower flange
position, which is connected to the stabilizer rear spar and not visible without detachment of the
fitting. Investigation determined that the corrosion is triggered by galvanic effect, due to a direct
contact between the horizontal stabilizer rear spar, made from CFRP (carbon fibre reinforced
plastic), and the aluminium rear attachment fitting.
This condition, if not detected and corrected, could lead to failure of the fitting and loss of one load
path of the horizontal stabilizer attachment, possibly resulting in reduced control of the aeroplane.
To address this potential unsafe condition, 328 Support Services GmbH (328 SSG) issued Service
Bulletin (SB) SB-328-55-557 and SB-328J-55-324 to provide instructions for inspection of the
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EASA AD No.: 2017-0239
affected area, replacement of the parts, and modification to improve corrosion behaviour by
incorporating of glass fibre layer.
For the reasons described above, this AD requires a one-time inspection of the horizontal stabilizer
rear bearing supports and, depending on findings, accomplishment of applicable corrective
action(s). This AD also requires a modification of the horizontal stabilizer rear spar, irrespective of
findings.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Note 1: 328 SSG SB-328-55-557 and SB-328J-55-324 are hereafter collectively referred to as ‘the
applicable SB’ in this AD.
Note 2: Group 1 aeroplanes are those with s/n 1005 to 1031 inclusive, which have rear bearing
supports Part Number (P/N) 001B551A1441000 installed. This part exhibits insufficient corrosion
resistance and static strength, resulting in reduced fatigue performance in the low cycle range.
Group 2 aeroplanes are those with s/n 1032 to s/n 3224 inclusive, which have rear bearing supports
P/N 001B551A1441002 (328-100) or P/N 001D551A1441000 (328-300) installed, having improved
properties.
Inspection:
(1) For Group 1 aeroplanes: Within 1 000 flight cycles (FC) or 8 months, whichever occurs first after
the effective date of this AD, inspect horizontal stabilizer rear bearing supports in accordance
with the instructions of the applicable SB.
(2) For Group 2 aeroplanes: Within 5 000 flight hours (FH) or 30 months, whichever occurs first
after the effective date of this AD, inspect the horizontal stabilizer rear bearing supports in
accordance with the instructions of the applicable SB.
Corrective Action(s):
(3) If, during the inspection as required by paragraphs (1) or (2) of this AD, as applicable, corrosion
or any other damage is detected, before next flight, replace the affected horizontal stabilizer
rear bearing supports in accordance with the instructions of the applicable SB.
Modification:
(4) Group 1 aeroplanes: Within 1 000 FC or 8 months, whichever occurs first after the effective
date of this AD, replace (unless already done as required by paragraph (3) of this AD) the
horizontal stabilizer rear bearing supports with new supports, and modify the horizontal
stabilizer rear spar in accordance with the instructions of the applicable SB.
(5) Group 2 aeroplanes: Within 5 000 FH or 30 months, whichever occurs first after the effective
date of this AD, modify the horizontal stabilizer rear spar in accordance with the instructions of
the applicable SB.
TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 3
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An agency of the European Union
EASA AD No.: 2017-0239
Reporting:
(6) Within 30 days after the inspection as required by paragraph (1) or (2) of this AD, as applicable,
report the inspection results (including no findings) to 328 SSG, in accordance with the
instructions of the applicable SB.
Parts Installation:
(7) Do not install on any aeroplane a horizontal stabilizer rear bearing support
P/N 001B551A1441000, as required by paragraph (7.1) or (7.2) of this AD, as applicable.
(7.1) For Group 1 aeroplanes: After replacement of the horizontal stabilizer rear bearing
supports as required by paragraph (3) or (4) of this AD, as applicable.
(7.2) For Group 2 aeroplanes: From the effective date of this AD.
Ref. Publications:
328 Support Services GmbH SB-328-55-557 dated 01 September 2017.
328 Support Services GmbH SB-328J-55-324 dated 01 September 2017.
The use of later approved revisions of these documents 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. This AD was posted on 24 October 2017 as PAD 17-150 for consultation until 21 November
2017. No comments were received during the consultation period.
3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,
Certification Directorate. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements in this AD, please
contact: 328 Support Services GmbH, Postfach 1252, D-82231 Wessling, Federal Republic of
Germany, Telephone: +49 (0)8153 88111 6666; Fax: +49 (0)8153 88111 6565,
E-mail gsc.op@328support.de.
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