Nachrichten für Luftfahrer 2018 Teil 2 (weicht ggf. von Druckversion ab)
EASA AD No.: 2012-0053R1
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Inspection:
(1) Initially within the threshold indicated in Table 1 of this AD and, thereafter, at intervals not to
exceed 26 months, accomplish a detailed visual inspection of the bogie pivot pins on the MLG
and CLG (for A340 aeroplanes only) and pivot pin bushes in accordance with the instructions of
the applicable inspection SB.
Table 1 – Initial Inspection
Bogie pivot pin condition Compliance Time
Bogie pivot pin fitted on MLG installed
on A330, A340-200 and A340-300
aeroplanes not having embodied:
Airbus modification 54500 in Within 26 months after 22 March 2011 [the
production or, effective date of EASA AD 2011-0040] or since the
Airbus SB A330-32-3212 in service or, aeroplane first flight, whichever occurs later, but
Airbus SB A340-32-4256 in service not before the accumulation of 12 months after
the aeroplane first flight.
Bogie pivot pin fitted on MLG and CLG
installed on A340-500 and A340-600
aeroplanes
Bogie pivot pin fitted on MLG on Within 26 months after 13 April 2012 [the
aeroplanes having embodied: effective date of EASA AD 2012-0053 original
Airbus modification 54500 in issue] or since the aeroplane first flight,
production or, whichever occurs later, but not before the
Airbus SB A330-32-3212 in service or, accumulation of 12 months after the aeroplane
Airbus SB A340-32-4256 in service first flight.
Note: Accomplishment of an overhaul of the MLG or CLG does not substitute the accomplishment
of an inspection as required by paragraph (1) of this AD.
Corrective Action(s):
(2) If, during any inspection as required by paragraph (1) of this AD, any bush is found cracked or
damaged, before next flight, accomplish the applicable corrective action(s) in accordance with
the instructions of the applicable inspection SB.
(3) If, during any inspection as required by paragraph (1) of this AD, degraded chrome plating on a
bogie pivot pin is found, before next flight, accomplish a Non-Destructive Test (NDT) inspection
of the affected bogie pivot pin in accordance with the instructions of the applicable inspection
SB.
(4) If, during any NDT inspection as required by paragraph (3) of this AD, the bogie pivot pin base
metal is found corroded, before next flight, accomplish the applicable corrective action(s) in
accordance with the instructions of the applicable inspection SB.
TE.CAP.00110-008 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 3 of 5
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2012-0053R1
Terminating Action:
(5) Accomplishment of corrective actions on an aeroplane, as required by paragraph (2) or (4) of
this AD, as applicable, does not constitute terminating action for the repetitive inspection
requirements of paragraph (1) of this AD for that aeroplane.
Modification of an aeroplane in accordance with the instructions of the applicable modification
SB constitutes terminating action for the repetitive inspections as required by paragraph (1) of
this AD for that aeroplane.
Credit:
(6) Inspections and corrective actions on an aeroplane, accomplished before the effective date of
this AD in accordance with the instructions of Airbus SB A330-32-3240 at original issue or
Revision 01, or SB A340-32-4281 at original issue, or SB A340-32-5096 at original issue, as
applicable, are acceptable for compliance with the initial requirements of paragraphs (1), (2),
(3) and (4) of this AD, as applicable, for that aeroplane.
Reporting:
(7) DELETED.
Ref. Publications:
Airbus SB A330-32-3240 Revision 02 dated 02 December 2011.
Airbus SB A340-32-4281 Revision 01 dated 02 December 2011.
Airbus SB A340-32-5096 Revision 01 dated 02 December 2011.
Airbus SB A330-32-3290 original issue dated 26 December 2017.
Airbus SB A330-32-3291 original issue dated 28 September 2018.
Airbus SB A340-32-4315 original issue dated 26 December 2017.
Airbus SB A340-32-4316 original issue dated 28 September 2018.
The use of later approved revisions of the above-mentioned 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. The original issue of this AD was posted on 16 February 2012 as PAD 12-016 for consultation
until 15 March 2012. The Comment Response Document can be found in the EASA Safety
Publications Tool, in the compressed (zipped) file attached to the record for this AD.
3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,
Certification Directorate. E-mail: ADs@easa.europa.eu.
TE.CAP.00110-008 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 4 of 5
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2012-0053R1
4. Information about any failures, malfunctions, defects or other occurrences, which may be
similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on
a product, part or appliance not affected by this AD, can be reported to the EU aviation safety
reporting system.
5. For any question concerning the technical content of the requirements in this AD, please
contact: AIRBUS – EIAL (Airworthiness Office), E-mail: airworthiness.A330-A340@airbus.com.
TE.CAP.00110-008 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 5 of 5
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2013-149R2 38144 Braunschweig
FAA AD 2018-22-10 - Amdt. 39-19483 Fax: +49-531-2355-5298
email: ad@LBA.de
MCDONNELL DOUGLAS 27.11.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: The Boeing Company
Hersteller: McDonnell Douglas Corporation
Muster: DC-10 / MD-11
Baureihen: DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F
(KC-10A und KDC-10), DC-10-40, DC-10-40F,
MD-10-10F, MD-10-30F,
MD-11 und MD-11F
Werknummern: Alle
Gerätenummer: 2835, EASA.IM.A.210, FAA TCDS A22WE
Revisionsstand:
Diese LTA ersetzt D-2013-149R1 vom 25.04.2016
Airworthiness Directive der ausländischen Behörde:
FAA AD 2018-22-10 - Amdt. 39-19483
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 2013-149R2 geführt.
Betrifft:
(ATA 28) Fuel - Fuel System - Review
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
FAA AD 2018-22-10 - Amdt. 39-19483 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-2013-149R2 Seite 1 von 1 544/2018
[Federal Register Volume 83, Number 216 (Wednesday, November 7, 2018)]
[Rules and Regulations]
[Pages 55610-55614]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-23822]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0510; Product Identifier 2017-NM-115-AD; Amendment 39-19483; AD
2018-22-10]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: We are superseding Airworthiness Directive (AD) 2016-04-16, which applied to all
The Boeing Company Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A
and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. AD
2016-04-16 required adding design features to detect electrical faults and to detect a pump running in
an empty fuel tank. This AD continues to require adding design features to detect electrical faults and
to detect a pump running in an empty fuel tank. This AD also provides optional terminating action for
certain requirements. This AD was prompted by a fuel system review conducted by the manufacturer.
We are issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective December 12, 2018.
The Director of the Federal Register approved the incorporation by reference of certain
publications listed in this AD as of December 12, 2018.
The Director of the Federal Register approved the incorporation by reference of certain other
publications listed in this AD as of April 15, 2016 (81 FR 12806, March 11, 2016).
ADDRESSES: For service information identified in this final rule, 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.
You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-
3195. It is also available on the internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0510.
1
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for
and locating Docket No. FAA-2018-0510; 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, the
regulatory evaluation, any comments received, and other information. The address for Docket
Operations (phone: 800-647-5527) is Docket Operations, 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: Serj Harutunian, Aerospace Engineer, Propulsion
Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5254; fax: 562-627-5210; email: serj.harutunian@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD
2016-04-16, Amendment 39-18410 (81 FR 12806, March 11, 2016) (“AD 2016-04-16”). AD 2016-
04-16 applied to all The Boeing Company Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-
10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-
11F airplanes. The NPRM published in the Federal Register on June 14, 2018 (83 FR 27718). The
NPRM was prompted by a fuel system review conducted by the manufacturer and a determination
that accomplishing new service information in conjunction with certain service information specified
in AD 2016-04-16 would terminate certain actions in related ADs. The NPRM proposed to continue
to require adding design features to detect electrical faults and to detect a pump running in an empty
fuel tank. The NPRM also proposed to provide optional terminating action for certain requirements.
We are issuing this AD to address the potential of ignition sources inside fuel tanks, which, in
combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of
the airplane.
Comments
We gave the public the opportunity to participate in developing this AD. The following presents
the comments received on the NPRM and the FAA's response to each comment.
Support for the NPRM
FedEx Express (FedEx) and Air Line Pilots Association, International (ALPA) provided their
concurrence with the NPRM. FedEx also pointed out that the NPRM affects 39 Model MD-10
airplanes and 57 Model MD-11 airplanes in the FedEx fleet.
Request To Clarify the Terminating Action Specified in Paragraph (k) of the Proposed AD
Boeing requested that we clarify the terminating action specified in paragraph (k) of the
proposed AD. Boeing agreed that the repetitive inspections and tests may be terminated upon
installation of the new connector design per the Boeing service bulletins cited in paragraph (k) of the
proposed AD (Boeing Service Bulletin DC10-28-264, dated May 15, 2015; and Boeing Service
Bulletin MD11-28-146, dated May 15, 2015). Boeing noted that those service bulletins were
approved by the Manager, Los Angeles ACO Branch. Boeing added that those service bulletins also
specify an additional condition for the terminating actions: the fault current detectors cited in
2
paragraphs (h)(1)(ii) and (h)(2)(ii) of the proposed AD must also be installed before the repetitive
actions are terminated. Boeing recommended that paragraph (k) of the proposed AD be revised to
clarify that the fault current detectors must be installed per paragraphs (h)(1)(ii) and (h)(2)(ii) of the
proposed AD in order to accomplish the terminating action per the Boeing service bulletins cited in
paragraph (k) of the proposed AD.
We agree with the commenter's request. Paragraph F., “Approval,” of Boeing Service Bulletin
DC10-28-264, dated May 15, 2015; and Boeing Service Bulletin MD11-28-146, dated May 15, 2015,
specifies that the actions in those service bulletins as well as the service bulletins specified in
paragraphs (h)(1)(ii) and (h)(2)(ii) of this AD terminate the actions required by paragraph (a) of AD
2002-13-10, Amendment 39-12798 (67 FR 45053, July 8, 2002) (“AD 2002-13-10”), paragraph (a)
of AD 2003-07-14, Amendment 39-13110 (68 FR 17544, April 10, 2003) (“AD 2003-07-14”), and
paragraph (j) of AD 2011-11-05, Amendment 39-16704 (76 FR 31462, June 1, 2011) (“AD 2011-11-
05”). We have revised paragraph (k) of this AD accordingly.
Request To Withdraw the NPRM
United Parcel Service (UPS) requested that we withdraw the NPRM. UPS pointed out that the
NPRM includes no new requirements or information. UPS indicated that no new requirements or
actions would create an undue burden on operators because existing internal paperwork and records
must then be revised to provide proof of compliance.
We acknowledge the commenter's concerns; however, we disagree with the request to withdraw
the NPRM. AD 2003-07-14 was affected by AD 2016-04-16 but was inadvertently left out of AD
2016-04-16. This AD corrects that oversight and includes AD 2003-07-14 as an affected AD.
Additionally, this AD provides new optional terminating actions that affect AD 2003-07-14 as well as
AD 2002-13-10 and AD 2011-11-05.
Request To Include Updated Service Information
UPS requested that we revise the NPRM to include a later revision of Boeing Trijet Special
Compliance Item Report MDC-02K1003. UPS pointed out that the new fuel pump housing assembly
that is created by installation of the new connectors was not added until Revision N of Boeing Trijet
Special Compliance Item Report MDC-02K1003. Additionally, UPS mentioned that Revision R of
Boeing Trijet Special Compliance Item Report MDC-02K1003 was in the approval process at the
time the comment was submitted.
We agree with the request to include the latest published version of Boeing Trijet Special
Compliance Item Report MDC-02K1003. We referred to Boeing Trijet Special Compliance Item
Report MDC-02K1003, Revision M, including Appendices A through D, dated July 25, 2014, as an
appropriate source of service information in the NPRM. Revision R of Boeing Trijet Special
Compliance Item Report MDC-02K1003, including Appendices A through D, dated May 9, 2018,
includes new part numbers for Critical Design Configuration Control Limitation (CDCCL) 28-2 and
updates certain special compliance items to include additional procedures for airplanes with a certain
configuration. We have added paragraph (l) to this AD to include Revision R of Boeing Trijet Special
Compliance Item Report MDC-02K1003, including Appendices B through D, dated May 9, 2018, as
an optional revision to paragraph (h)(3) of this AD, and we have redesignated subsequent paragraphs
accordingly. We are considering further rulemaking to require revising the maintenance or inspection
program to include Revision R of Boeing Trijet Special Compliance Item Report MDC-02K1003,
including Appendices B through D, dated May 9, 2018.
3
Conclusion
We reviewed the relevant data, considered the comments received, and determined that air safety
and the public interest require adopting this AD with the changes described previously, and minor
editorial changes. We have determined that these minor changes:
• Are consistent with the intent that was proposed in the NPRM for addressing the unsafe
condition; and
• Do not add any additional burden upon the public than was already proposed in the NPRM.
We also determined that these changes will not increase the economic burden on any operator or
increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed the following Boeing service information.
• Boeing Alert Service Bulletin DC10-28A253, dated June 5, 2014; and Boeing Alert Service
Bulletin MD11-28A133, dated June 5, 2014. This service information describes procedures
for replacing the fuel pump control relays with fault current detectors and changing the fuel
tank boost/transfer pump wire termination. These documents are distinct since they apply to
different airplane models.
• Boeing Service Bulletin DC10-28-256, dated June 24, 2014; and Boeing Service Bulletin
MD11-28-137, dated June 24, 2014. This service information describes procedures for
changing the fuel pump control and indication system wiring. These documents are distinct
since they apply to different airplane models.
• Boeing Trijet Special Compliance Item Report MDC-02K1003, Revision M, including
Appendices A through D, dated July 25, 2014; and Boeing Trijet Special Compliance Item
Report MDC-02K1003, Revision R, including Appendices A through D, dated May 9, 2018;
which include CDCCLs, ALIs, and short-term extensions in Appendices B, C, and D,
respectively. This service information describes fuel ALIs that address ignition sources. These
documents are distinct since Revision R includes additional requirements.
• Boeing Service Bulletin DC10-28-264, dated May 15, 2015, and Boeing Service Bulletin
MD11-28-146, dated May 15, 2015. This service information describes procedures for
replacement of the fuel pump housing electrical connector, associated wires, fuel tank feed-
through components, and installing sealed terminal lugs on the fuel pump wiring, or
replacement of the fuel pump housing, associated wires, fuel tank feed-through components,
and installing sealed terminal lugs on the fuel pump. These documents are distinct since they
apply to different airplane models.
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 the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 341 airplanes of U.S. registry. We estimate the following costs
to comply with this AD:
4
Estimated Costs for Required Actions
Action Labor cost Parts Cost per Cost on U.S.
cost product operators
Installing design features using a 152 work-hours × $137,500 $150,420 $51,293,220.
method approved by the FAA $85 per hour =
(retained actions from AD 2016-04- $12,920
16)
Installing design features using service 98 work-hours × 109,000 117,330 40,009,530.
information (retained optional actions $85 per hour =
from AD 2016-04-16) $8,330
Estimated Costs for Optional Terminating Actions
Action Labor cost Parts cost Cost per
product
Option 1: Replace connectors for Model DC- 68 work-hours × $85 per $54,842 $60,622.
10 and MD-10 (122 airplanes) hour = $5,780
Option 1: Replace connectors for Model MD- 59 work-hours × $85 per $67,031 $72,046.
11 (124 airplanes) hour = $5,015
Option 2: Replace fuel pump housings for Up to 81 work-hours × Up to Up to
Model DC-10 and MD-10 (122 airplanes) $85 per hour = $6,885 $54,842 $61,727.
Option 2: Replace fuel pump housings for Up to 77 work-hours × Up to Up to
Model MD-11 (124 airplanes) $85 per hour = $6,545 $67,031 $73,576.
We have received no definitive data that would enable us to provide cost estimates for the on-
condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III,
Section 44701, “General requirements.” Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses an unsafe condition that is likely
to exist or develop on products identified in this rulemaking action.
This AD is issued in accordance with authority delegated by the Executive Director, Aircraft
Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance
of ADs is normally a function of the Compliance and Airworthiness Division, but during this
transition period, the Executive Director has delegated the authority to issue ADs applicable to
transport category airplanes and associated appliances to the Director of the System Oversight
Division.
5
Regulatory Findings
We have determined that this AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States, on the relationship between the
national government and the States, or on the distribution of power and responsibilities among the
various levels of government.
For the reasons discussed above, I certify that this AD:
(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 removing Airworthiness Directive (AD) 2016-04-16, Amendment
39-18410 (81 FR 12806, March 11, 2016), and adding the following new AD:
6
