Nachrichten für Luftfahrer 2012 Teil II (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig
D-2012-061 Fax: +49-531-2355-725
email: ad@lba.de
AIRBUS Datum der Bekanntgabe: 20.01.2012
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Airbus
Hersteller: Airbus, Airbus Industrie
Muster: A330, A340
Baureihen: A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, A330-
243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, A330-
341, A330-342, A330-343, A340-211, A340-212, A340-213, A340-311, A340-
312 und A340-313
Werknummern: Alle
Nicht betroffen sind Flugzeuge des Musters Airbus A330, bei denen die Airbus
Modifikation 201654 während der Herstellung oder das Airbus Service Bulletin
A330-27-3156 nach der Indienststellung durchgeführt wurden
Gerätenummer: 2849, 2850, EASA.A.004, EASA.A.015
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2011-0199 vom 27.10.2011
Betrifft:
(ATA 22, 27) Auto Flight / Flight Controls - Flight Control Primary Computer (FCPC) - Modification / Replacement
Maßnahmen und Fristen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten EASA Airworthiness
Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen. Alle erforderlichen
Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und innerhalb der
vorgesehenen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle Abweichungen von
den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das
Luftfahrt-Bundesamt.
Alle anzuwendenden Fristen sind der genannten EASA Airworthiness Directive zu entnehmen. Die Laufzeit aller
anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten EASA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA AD 2011-0199 vom 27.10.2011.
Zugehörige technische Dokumente:
Hinweis: Die Anwendung von nachfolgenden Ausgaben bzw. Revisionsständen der genannten zugehörigen technischen Dokumente ist zulässig, wenn dies nach
der Airworthiness Directive der ausländischen Behörde ausdrücklich gestattet ist oder wenn diese von der ausländischen Behörde in Bezug auf die referenzierte
Airworthiness Directive genehmigt worden sind.
1. Airbus Service Bulletin A330-27-3176 vom 26.07.2011
2. Airbus Service Bulletin A330-27-3177 [wird noch herausgegeben]
3. Airbus Service Bulletin A340-27-4162 [wird noch herausgegeben]
4. Airbus Service Bulletin A340-27-4174 [wird noch herausgegeben]
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der Sicherheit des Luftverkehrs, das in diesem Fall
das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es erforderlich, die sofortige Vollziehung dieser Lufttüchtigkeitsanweisung
anzuordnen.
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder zur Niederschrift beim
Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge-
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
D-2012-061 Seite 1 von 1 033/2012
EASA AD No : 2011-0199
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2011-0199
Date: 27 October 2011
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EC) No 216/2008 on behalf of the European Community, 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 EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 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 [EC
2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
Type Approval Holder’s Name : Type/Model designation(s) :
AIRBUS A330 and A340-200/-300 aeroplanes
TCDS Number : EASA.A.004 and EASA.A.015
Foreign AD : Not applicable
Supersedure : None
Auto Flight / Flight Controls – Flight Control Primary Computer
ATA 22, 27
(FCPC) – Modification / Replacement
Manufacturer(s): Airbus (formerly Airbus Industrie)
Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243,
A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323,
A330-341, A330-342 and A330-343 aeroplanes, all manufacturer serial numbers,
except those on which Airbus modification 201654 has been embodied in
production, or Airbus Service Bulletin (SB) A330-27-3156 has been incorporated
in service, and
Airbus A340-211, A340-212, A340-213, A340-311, A340-312 and A340-313
aeroplanes, all manufacturer serial numbers.
Reason: It has been determined that, when there are significant differences between all
airspeed sources, the flight controls of an Airbus A330 or A340 aeroplane will
revert to alternate law, the autopilot (AP) and the auto-thrust (A/THR)
automatically disconnect, and the Flight Directors (FD) bars are automatically
removed.
Further analyses have shown that, after such an event, if two airspeed sources
become similar while still erroneous, the flight guidance computers will display
the FD bars again, and enable the re-engagement of AP and A/THR. However, in
some cases, the AP orders may be inappropriate, such as possible abrupt pitch
command.
In order to prevent such events which may, under specific circumstances,
constitute an unsafe condition, EASA issued AD 2010-0271 to require an
amendment of the Flight Manual to ensure that flight crews apply the appropriate
operational procedure.
EASA Form 110 Page 1/3
EASA AD No : 2011-0199
Since that AD was issued, new FCPC software standards have been developed
that will inhibit autopilot engagement under unreliable airspeed conditions.
This AD requires software standard upgrade of the three FCPCs by either
modification or replacement, as follows:
- software standard P11A/M20A on FCPC 2K2 hardware for A330-200/-300
aeroplanes with electrical rudder, through Airbus Service Bulletin (SB)
A330-27-3176,
- software standard P12A/M21A on FCPC 2K1 hardware and M21A on FCPC
2K0 hardware for A330-200/-300 aeroplanes with mechanical rudder, through
Airbus SB A330-27-3177,
- software standard L22A on FCPC 2K1 hardware and L22A on FCPC 2K0
hardware for A340-200/-300 aeroplanes with mechanical rudder, through Airbus
SB A340-27-4174, and
- software standard L21A on FCPC 2K2 hardware for A340-300 aeroplanes with
electrical rudder, through Airbus SB A340-27-4162.
Embodiment of these FCPC software standards constitutes terminating action for
the A330 Airplane Flight Manual (AFM) Temporary Revisions (TR) 149 and A340
AFM TR 150 required by EASA AD 2010-0271.
Some of the Airbus SBs listed above may not be available at the expected date
of issuance of the Final AD for this subject. It is expected that this AD will be
revised when all the related SBs have been published. Due to the time needed
for certification of the remaining FCPC software standards and the associated
non-availability of some SBs, the requirements of EASA AD 2010-0271 will not
be cancelled yet.
Effective Date: 10 November 2011
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
Within 10 months after the effective date of this AD, modify or replace the three
Time(s):
FCPCs, as specified in Table 1 of this AD, in accordance with the instructions of
Airbus SB A330-27-3176, or SB A330-27-3177, or SB A340-27-4162, or SB
A340-27-4174, as applicable to aeroplane type and model.
Table 1 – Software Standard updates
Affected Software Standard update(s) Airbus SB
aeroplanes
A330-200/-300 software standard P11A/M20A on SB A330-27-3176
aeroplanes with FCPC 2K2 hardware
electrical rudder
A330-200/-300 software standard P12A/M21A on SB A330-27-3177
aeroplanes with FCPC 2K1 hardware, and
[to be issued]
mechanical rudder software standard M21A on FCPC
2K0 hardware
A340-200/-300 software standard L22A on FCPC SB A340-27-4162
aeroplanes with 2K1 hardware, and
[to be issued]
mechanical rudder software standard L22A on FCPC
2K0 hardware
A340-300 software standard L21A on FCPC SB A340-27-4174
aeroplanes with 2K2 hardware
[to be issued]
electrical rudder
EASA Form 110 Page 2/3
EASA AD No : 2011-0199
Ref. Publications: Airbus SB A330-27-3176 original issue dated 26 July 2011.
Airbus SB A330-27-3177 [to be issued]
Airbus SB A340-27-4162 [to be issued]
Airbus SB A340-27-4174 [to be issued]
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 02 August 2011 as PAD 11-081 for consultation until
30 August 2011. The Comment Response Document can be found at
http://ad.easa.europa.eu/.
3. Enquiries regarding this AD should be referred to the Safety Information
Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements in this
AD, please contact: AIRBUS – Airworthiness Office – EAL;
E-mail: airworthiness.A330-A340@airbus.com
EASA Form 110 Page 3/3
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig
D-2012-062 Fax: +49-531-2355-725
email: ad@lba.de
BOEING Datum der Bekanntgabe: 23.01.2012
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: The Boeing Company
Hersteller: The Boeing Company
Muster: BOEING 777
Baureihen: 777-200, 777-200LR, 777-300 und 777-300ER
Werknummern: Gemäß Boeing Service Bulletin 777-24-0102, Revision 1 vom 17.06.2010 und
Boeing Special Attention Service Bulletin 777-29-0032 vom 09.08.2007
Gerätenummer: 2863, EASA.IM.A.003
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2011-21-03 - Amdt. 39-16826
Betrifft:
(ATA 29/ 24): Hydraulic power/ Electrical power - External Power Connector - Installation
Maßnahmen und Fristen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten FAA Airworthiness Directive
und den genannten technischen Mitteilungen des Herstellers zu entnehmen. Alle erforderlichen Maßnahmen zur
Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und innerhalb der vorgesehenen Fristen
auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle Abweichungen von den Maßnahmen und
Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Alle anzuwendenden Fristen sind der genannten FAA Airworthiness Directive zu entnehmen. Die Laufzeit aller
anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten FAA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2011-21-03 - Amdt. 39-16826.
Zugehörige technische Dokumente:
Hinweis: Die Anwendung von nachfolgenden Ausgaben bzw. Revisionsständen der genannten zugehörigen technischen Dokumente ist zulässig, wenn dies nach
der Airworthiness Directive der ausländischen Behörde ausdrücklich gestattet ist oder wenn diese von der ausländischen Behörde in Bezug auf die referenzierte
Airworthiness Directive genehmigt worden sind.
1. Boeing Service Bulletin 777-24-0102 Revision 1 vom 17.06.2010
2. Boeing Special Attention Service Bulletin 777-29-0032 vom 09.08.2007
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der Sicherheit des Luftverkehrs, das in diesem Fall
das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es erforderlich, die sofortige Vollziehung dieser Lufttüchtigkeitsanweisung
anzuordnen.
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder zur Niederschrift beim
Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge-
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
D-2012-062 Seite 1 von 1 032/2012
[Federal Register Volume 76, Number 197 (Wednesday, October 12, 2011)]
[Rules and Regulations]
[Pages 63163-63167]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-25754]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1312; Directorate Identifier 2010-NM-220-AD; Amendment 39-16826;
AD 2011-21-03]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 777-200, -200LR, -300, and -300ER
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This
AD requires installing foreign object debris (FOD) rubber shields over the primary and secondary
external power connectors for certain airplanes, and wrapping silicone tape around the hydraulic tube
for certain other airplanes. This AD was prompted by a report of a fire in the main equipment center
due to failure of an external power connector, which caused high-temperature arcing and subsequent
splatter of molten copper on an adjacent hydraulic tube, creating a hole in the tube and spraying
hydraulic fluid into the power connector, resulting in a fire. In addition there were several reports of
overheating or arcing of external power connectors, and one report of a fire due to arcing caused by
FOD. We are issuing this AD to prevent FOD from entering the primary and secondary external
power connectors, which could result in overheating or arcing and consequent fire in the main
equipment center.
DATES: This AD is effective November 16, 2011.
The Director of the Federal Register approved the incorporation by reference of certain
publications listed in the AD as of November 16, 2011.
ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes,
Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-
2207; telephone 206-544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at the FAA, call 425-227-1221.
1
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at
the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-5527) is Document
Management Facility, 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: Georgios Roussos, Aerospace Engineer, Systems
and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98057-3356; phone: (425) 917-6482; fax: (425) 917-6590; e-mail:
georgios.roussos@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an
airworthiness directive (AD) that would apply to the specified products. That NPRM published in the
Federal Register on January 18, 2011 (76 FR 2846). That NPRM proposed to require installing
foreign object debris (FOD) rubber shields over the primary and secondary external power connectors
for certain airplanes, and wrapping fire-resistant silicone tape around the hydraulic tube for certain
other airplanes.
Comments
We gave the public the opportunity to participate in developing this AD. The following presents
the comments received on the proposal and the FAA's response to each comment.
Support for the NPRM
American Airlines has accomplished the modifications on the majority of its fleet, and has no
objection to the actions and compliance times in the NPRM (76 FR 2846, January 18, 2011). The
National Transportation Safety Board supports the NPRM.
Request To Use Latest Production Hydraulic Tube
Japan Airlines (JAL), Continental Airlines, and All Nippon Airways (ANA) asked that operators
be allowed to use the latest production hydraulic tube having part number (P/N) 272W4190-192,
which already has the silicone tape pre-wrapped, in lieu of modifying the existing hydraulic tube
assembly by installing the silicone tape in accordance with Boeing Special Attention Service Bulletin
777-29-0032, dated August 9, 2007. JAL also noted a concern about procuring the hydraulic tube.
We do not agree with the request to use the latest production hydraulic tube as an acceptable
alternative to installing the silicone tape. Based on the latest information received from Boeing
engineering, the following applies to any possible hydraulic tube replacement: Any hydraulic tube
having P/N 272W4190-192 (as specified in Boeing Special Attention Service Bulletin 777-29-0032,
dated August 9, 2007), cannot be a direct replacement for the existing part. Hydraulic tubes having
P/Ns 272W4190-93, -168, and -192 for production installation require the use of permaswage fittings
on either side of the tube. Removal of the tube for its replacement requires that the tube be physically
cut past the permaswage fitting, thus making it longer than the original production part. We have
made no change to the AD in this regard.
2
Request To Include Instructions for Continued Airworthiness
Continental and ANA also noted that the service information does not contain proper instructions
for continued airworthiness (ICAs) to install the tape on the new line, or inclusion of the equivalent
production part number in the Boeing 777 illustrated parts catalog (IPC). Continental added that a
pre- and post-service bulletin configuration should be included to provide instructions to use a newer
part or to accomplish the actions specified in the service information again.
We acknowledge the commenters' concern, but we do not agree. The Boeing ICAs do include a
statement indicating that the production tubes are reworked by using the procedures in Boeing
Special Attention Service Bulletin 777-29-0032, dated August 9, 2007. Since there is not direct
replacement with a production tube, we are working with Boeing to identify additional information
necessary in support of replacing the hydraulic tube. We have made no change to the AD in this
regard.
Request To Include Information Notices
United Airlines asked that we revise the NPRM (76 FR 2846, January 18, 2011) to refer to
Boeing Service Bulletin Information Notices 777-29-0032 IN 01, dated November 29, 2007, and
777-29-0032 IN 02, dated December 11, 2008, which include clarifications to the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 777-29-0032, dated August 9, 2007.
We acknowledge that these information notices may be useful to operators to clarify certain
instructions specified in Boeing Special Attention Service Bulletin 777-29-0032, dated August 9,
2007. However, Boeing has provided these notices to operators. We do not reference information
notices in ADs because those documents are not FAA-reviewed. In addition, the information notices
do not contain technical information and are not necessary to accomplish the actions required by the
AD. We have made no change to the AD in this regard.
Request To Change the Applicability
Boeing requested that the applicability section in the NPRM (76 FR 2846, January 18, 2011) be
changed. Boeing stated that the applicability should be limited to the airplanes identified in the
referenced service information, which include only those airplanes on which the modifications
required by the AD have not been accomplished in production.
We agree with the commenter for the reason provided and have limited the applicability section
in this AD accordingly, in lieu of specifying ''all'' airplanes of the affected model.
Request To Clarify Tape Qualities
Boeing asked that we delete the term ''fire-resistant,'' which describes ''silicone tape,'' as specified
in the Summary section, Relevant Service Information section, and paragraph (g)(2) of the NPRM
(76 FR 2846, January 18, 2011). Boeing stated that the product data sheet identifies the tape as ''high
temperature arc- and track-resistant tape,'' but not ''fire-resistant.''
We agree with the commenter for the reason provided. However, the term ''fire-resistant'' was
used in the NPRM (76 FR 2846, January 18, 2011) because it is specified as such in the referenced
service information. We have removed it from the Summary section and paragraph (g)(2) of this AD.
The Relevant Service Information section of the preamble does not reappear in the final rule.
Request To Clarify Terminology of Tape Dimensions
Boeing asked that we change the language in the ''Exception to Service Information'' section in
paragraph (h) of the NPRM (76 FR 2846, January 18, 2011) as follows: ''Figure 1 of the
Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-29-0032, dated
3
August 9, 2007, does not identify the units of the dimensions of the silicone tape installed on the
hydraulic tube; those dimensions are identified in inches.'' Boeing noted that the dimensions of the
tape are identified, but the units of the dimensions are missing. Boeing added that, although the tape
can be used as ''electrical'' tape, for this application it is more appropriate to identify it as ''silicone''
tape.
We agree with the commenter for the reasons provided. The word ''electrical'' was used in the
NPRM (76 FR 2846, January 18, 2011) because it is specified as such in the referenced service
information. We have changed paragraph (h) of this AD to reiterate the commenter's suggested
language.
Request To Provide Additional Credit
Boeing asked that the service information specified in paragraph (i) of the NPRM (76 FR 2846,
January 18, 2011) under ''Credit for Actions Accomplished in Accordance with Previous Service
Information'' be changed to include Boeing Special Attention Service Bulletin 777-29-0032, dated
August 9, 2007 (referred to in the NPRM as the service information to use for installing the silicone
tape). Boeing stated that the modification accomplished by this service bulletin before the effective
date of the AD is identical to the modification accomplished by this service bulletin after the effective
date of the AD.
We do not agree that the subject service bulletin should be added to paragraph (i) of this AD.
Operators are already given credit for previously accomplished actions as allowed by the phrase in
paragraph (f) of this AD which states the following: ''Comply with this AD within the compliance
times specified, unless already done.'' We have made no change to the AD in this regard.
Request To Exclude Certain Proposed Actions
Delta Airlines asked that Boeing Special Attention Service Bulletin 777-29-0032, dated August
9, 2007, be excluded from the NPRM (76 FR 2846, January 18, 2011). Delta stated that since the root
cause of the external power connector fires and overheating was related to foreign object debris
(FOD) shorting out the external power connector inside the airplane, once the FOD shields are
installed per Boeing Service Bulletin 777-24-0102, Revision 1, dated June 17, 2010, the protective
tape identified in Boeing Special Attention Service Bulletin 777-29-0032, dated August 9, 2007,
serves no purpose. Delta added that if damage to the hydraulic tubing is still a concern even after
accomplishment of this service bulletin, a routing change to the hydraulic tubing would be a better
solution to protecting the tubing from a fire/overheat condition. Delta noted that the tape being
installed is not fireproof, only fire-resistant. Delta also stated that the instructions for installing the
tape specified in Boeing Special Attention Service Bulletin 777-29-0032, dated August 9, 2007,
would be difficult to comply with. Subsequent inspections of the tape installation to ensure
compliance with the NPRM would also be difficult when judging the overlap and number of tape
wraps, since the tape installation is based on the amount of stretch and a percentage of overlap.
We do not agree to remove Boeing Special Attention Service Bulletin 777-29-0032, dated
August 9, 2007, from this AD. Installation of the FOD shields is not the only action necessary to
address the identified unsafe condition. FOD shields alone do not resolve the potential for
overheating and arcing of the electrical connectors. Based on our evaluation, we have determined that
the connector design, lack of proper connector maintenance actions, and the proximity of the
hydraulic tubing to the connectors can result in a fire; therefore, accomplishing the actions required
by this AD will minimize the threat of fire on the airplane.
Additionally, although the silicone tape is not fireproof, installing the tape provides an
acceptable level of protection to the hydraulic tubing in the event of overheating or arcing of the
connectors. The procedures for installing the tape are not difficult for compliance and include easy
access and liberal application of the tape; several operators have already done this modification and
did not encounter any problems. Further, it is the responsibility of operators to maintain the AD-
4
mandated configuration, and this can be done using the procedures specified in Boeing Special
Attention Service Bulletin 777-29-0032, dated August 9, 2007. In light of these factors, we have
made no change to the AD.
Conclusion
We reviewed the relevant data, considered the comments received, and determined that air safety
and the public interest require adopting the AD with the changes described previously. We have
determined that these changes will neither increase the economic burden on any operator nor increase
the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 126 airplanes of U.S. registry. We estimate the following
costs to comply with this AD:
Estimated Costs
Action Labor cost Parts Cost Number of Fleet Cost
cost per airplanes
product affected
Install FOD 6 work-hour $134 $644 124 $79,856
rubber shields X $85 per
hour = $510
Wrap silicone 2 work-hour $0 $170 126 $21,420
tape X $85 per
hour = $170
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.
Regulatory Findings
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
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