Airworthiness Directives; The Boeing Company Airplanes, 57083-57086 [2015-23539]
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Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations
four occurrences, and adding in its
place ‘‘AU–1’’; and
■ d. Paragraph (g), by removing, ‘‘the
Chief Health, Safety and Security
Officer’’, and adding in its place ‘‘AU–
1’’; and by removing ‘‘the Office of
Health, Safety and Security’’ and adding
in its place ‘‘AU–1’’.
§ 1046.5
[Amended]
5. Section 1046.5(c) is amended by
removing ‘‘the Office of Health, Safety
and Security’’, two occurrences, and
adding in both places, ‘‘AU–1’’.
■
§ 1046.13
[Amended]
6. Section 1046.13(b)(3) is amended
by removing ‘‘the Chief Medical
Officer’’ and adding in its place ‘‘AU–
1’’.
■
§ 1046.15
[Amended]
7. Section 1046.15 is amended in:
a. Paragraph (c) introductory text, by
removing ‘‘the Office of Health, Safety
and Security’’ and adding in its place
‘‘AU–1’’; and in paragraph (c)(1) by
removing ‘‘The Office of Health, Safety
and Security’’ and adding in its place
‘‘AU–1’’; and
■ b. Paragraphs (c)(2), (c)(3), (c)(4)
introductory text, (c)(4)(iii), (c)(5), (c)(6)
introductory text, (c)(7) four
occurrences, (c)(8) and (d) two
occurrences, by removing ‘‘the Office of
Health, Safety and Security’’ and adding
in its place ‘‘AU–1’’.
■
■
§ 1046.17
[Amended]
8. Section 1046.17 is amended in
paragraph (k)(6) by removing ‘‘the Office
of Health, Safety and Security’’ and
adding in its place ‘‘AU–1’’.
■
[FR Doc. 2015–24083 Filed 9–21–15; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA–2015–0245; Directorate
Identifier 2014–NM–135–AD; Amendment
39–18268; AD 2015–19–06]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
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AGENCY:
We are superseding
Airworthiness Directive (AD) 2012–24–
10 for certain The Boeing Company
Model 747–400 and –400F series
SUMMARY:
13:50 Sep 21, 2015
This AD is effective October 27,
2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 27, 2015.
DATES:
For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0245.
ADDRESSES:
Examining the AD Docket
14 CFR Part 39
VerDate Sep<11>2014
airplanes. AD 2012–24–10 required
installing new software, replacing the
duct assembly with a new duct
assembly, making wiring changes, and
routing certain wire bundles. This new
AD retains the requirements of AD
2012–24–10 and requires installing a
new or serviceable pressure switch
bracket and altitude pressure switch.
This new AD also adds an airplane to
the applicability. This AD was
prompted by reports of intermittent or
blank displays of a certain integrated
display unit (IDU) that were due to an
intermittent false electrical ground that
was not addressed by the software
installation or wiring changes required
by AD 2012–24–10. We are issuing this
AD to prevent IDU malfunctions, which
could affect the ability of the flightcrew
to read primary displays for airplane
attitude, altitude, or airspeed, and
consequently reduce the ability of the
flightcrew to maintain control of the
airplane.
Jkt 235001
You may examine the AD docket on
the Internet at https://
www.regulations.govby searching for
and locating Docket No. FAA–2015–
0245; 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
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
PO 00000
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57083
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Francis Smith, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6596;
fax: 425–917–6591; email:
Francis.Smith@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–24–10,
Amendment 39–17280 (77 FR 73908,
December 12, 2012). AD 2012–24–10
applied to certain The Boeing Company
Model 747–400 and –400F series
airplanes. The NPRM published in the
Federal Register on February 18, 2015
(80 FR 8568). The NPRM was prompted
by reports of intermittent or blank
displays of a certain IDU that were due
to an intermittent false electrical ground
that was not addressed by the software
installation or wiring changes required
by AD 2012–24–10.
The NPRM (80 FR 8568, February 18,
2015) proposed to retain the
requirements of AD 2012–24–10. The
NPRM also proposed to require
installing a new or serviceable pressure
switch bracket and altitude pressure
switch, and add an airplane having
variable number RT061 as Group 21 to
the applicability of the existing AD. We
are issuing this AD to prevent IDU
malfunctions, which could affect the
ability of the flightcrew to read primary
displays for airplane attitude, altitude,
or airspeed, and consequently reduce
the ability of the flightcrew to maintain
control of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM (80 FR 8568,
February 18, 2015) and the FAA’s
response.
Request To Clarify Purpose of Altitude
Pressure Switch
Boeing requested that we revise the
wording in the Discussion section to
clarify that the altitude pressure switch
provides an independent and redundant
signal to the equipment cooling threeway valve. Boeing explained that the
logic to transition the three-way valve
through an altitude of 25,000 feet was
already present through a signal from
the environmental control system
miscellaneous card (ECSMC). The
commenter added that the logic
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Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations
redundancy is described correctly
elsewhere in the NPRM (80 FR 8568,
February 18, 2015).
We agree with the commenter’s
request because changing the wording
clarifies the intent of Boeing Special
Attention Service Bulletin 747–21–
2533, dated February 13, 2014, which
describes procedures for installing an
altitude pressure switch on the forward
side of the station 400 bulkhead for the
three-way valve of the equipment
cooling system. We have revised the
description of the service information,
which is provided in the Related
Service Information under 1 CFR part 51
section in this final rule.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (80 FR 8568,
February 18, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (80 FR 8568,
February 18, 2015).
Related Service Information Under 1
CFR Part 51
Boeing has issued the following
service information.
• Boeing Alert Service Bulletin 747–
21A2523, Revision 2, dated June 7,
2013. This service information describes
procedures for changing the wiring and
operating logic of the equipment cooling
three-way valve and replacing the
existing duct assembly with a new duct
assembly on the main distribution
manifold of the air conditioning system.
• Boeing Special Attention Service
Bulletin 747–21–2532, dated February
13, 2014. This service information
describes procedures for installing an
altitude pressure switch on the forward
side of the station 400 bulkhead for the
three-way valve of the equipment
cooling system.
• Boeing Special Attention Service
Bulletin 747–21–2533, dated February
13, 2014. This service information
describes procedures for adding a
second altitude signal to the switching
logic for the three-way valve to provide
a second, independent altitude signal
for the equipment cooling system.
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 of
this AD.
Costs of Compliance
We estimate that this AD affects 33
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Cost per
product
Labor cost
Duct assembly and replacement wiring changes (retained actions from AD 2012–24–10, Amendment
39–17280 (77 FR 73908, December 12, 2012).
Software changes (retained actions from AD 2012–24–
10, Amendment 39–17280 (77 FR 73908, December
12, 2012).
Altitude pressure switch installation (new action) ...........
44 work-hours × $85 per hour = $3,740
$20,121
$23,861
$787,413
3 work-hours × $85 per hour = $255 .....
0
255
8,415
13 work-hours × $85 per hour = $1,105
5,230
6,335
209,055
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According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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
VerDate Sep<11>2014
13:50 Sep 21, 2015
Jkt 235001
Parts cost
Cost on U.S.
operators
Action
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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.
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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)
2012–24–10, Amendment 39–17280 (77
FR 73908, December 12, 2012), and
adding the following new AD:
■
2015–19–06 The Boeing Company:
Amendment 39–18268; Docket No.
FAA–2015–0245; Directorate Identifier
2014–NM–135–AD.
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Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations
(a) Effective Date
This AD is effective October 27, 2015.
(b) Affected ADs
This AD replaces AD 2012–24–10,
Amendment 39–17280 (77 FR 73908,
December 12, 2012).
(c) Applicability
This AD applies to The Boeing Company
Model 747–400 and -400F series airplanes,
certificated in any category, as identified in
Boeing Alert Service Bulletin 747–21A2523,
Revision 2, dated June 7, 2013.
(d) Subject
Air Transport Association (ATA) of
America Code 21, Air Conditioning; 31,
Instruments.
(e) Unsafe Condition
This AD was prompted by reports of
intermittent or blank displays of a certain
integrated display unit (IDU) in the flight
deck. We are issuing this AD to prevent IDU
malfunctions, which could affect the ability
of the flightcrew to read primary displays for
airplane attitude, altitude, or airspeed, and
consequently reduce the ability of the
flightcrew to maintain control of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Software Update, With Revised
Service Information
This paragraph restates the requirements of
paragraph (g) of AD 2012–24–10,
Amendment 39–17280 (77 FR 73908,
December 12, 2012), with revised service
information. Within 12 months after January
16, 2013 (the effective date of AD 2012–24–
10), except as provided by paragraph (j) of
this AD: Install integrated display system
software, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–21A2523, Revision 1,
dated October 3, 2011; or Boeing Alert
Service Bulletin 747–21A2523, Revision 2,
dated June 7, 2013. As of the effective date
of this AD, only Boeing Alert Service Bulletin
747–21A2523, Revision 2, dated June 7,
2013, may be used to accomplish the actions
required by this paragraph.
Note 1 to paragraphs (g) and (j) of this AD:
Boeing Alert Service Bulletin 747–21A2523,
Revision 1, dated October 3, 2011; and
Boeing Alert Service Bulletin 747–21A2523,
Revision 2, dated June 7, 2013; refer to
Boeing Service Bulletin 747–31–2426, dated
July 29, 2010 (for airplanes with Rolls-Royce
engines); Boeing Service Bulletin 747–31–
2427, dated July 29, 2010 (for airplanes with
General Electric engines); and Boeing Service
Bulletin 747–31–2428, dated July 29, 2010
(for airplanes with Pratt & Whitney engines);
as additional sources of guidance for the
software installation specified by paragraph
(g) of this AD.
(h) Retained Duct Assembly Replacement
and Wiring Changes, With Revised Service
Information
This paragraph restates the requirements of
paragraph (h) of AD 2012–24–10,
VerDate Sep<11>2014
13:50 Sep 21, 2015
Jkt 235001
Amendment 39–17280 (77 FR 73908,
December 12, 2012), with revised service
information. Within 60 months after January
16, 2013 (the effective date of AD 2012–24–
10), except as provided by paragraph (j) of
this AD: Replace the duct assembly with a
new duct assembly, do wiring changes, and
route certain wire bundles, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–21A2523,
Revision 1, dated October 3, 2011; or Boeing
Alert Service Bulletin 747–21A2523,
Revision 2, dated June 7, 2013. As of the
effective date of this AD, only Boeing Alert
Service Bulletin 747–21A2523, Revision 2,
dated June 7, 2013, may be used to
accomplish the actions required by this
paragraph.
(i) New Installation of Pressure Switch
Bracket and Altitude Pressure Switch
Within 60 months after the effective date
of this AD: Install a new or serviceable
pressure switch bracket and a new or
serviceable altitude pressure switch on the
forward side of the station 400 bulkhead, do
wiring changes, route certain wire bundles,
install a new hose assembly, and perform a
leak check and a functional logic test, in
accordance with the Accomplishment
Instructions of the service information
specified in paragraph (i)(1) or (i)(2) of this
AD, as applicable.
(1) For Model 747–400F series airplanes:
Boeing Special Attention Service Bulletin
747–21–2532, dated February 13, 2014.
(2) For Model 747–400BCF series
airplanes: Boeing Special Attention Service
Bulletin 747–21–2533, dated February 13,
2014.
(j) Actions for Group 21 Airplanes
For Group 21 airplanes, as identified in
Boeing Alert Service Bulletin 747–21A2523,
Revision 2, dated June 7, 2013, do the actions
specified in paragraphs (j)(1) and (j)(2) of this
AD, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–21A2523, Revision 2, dated June 7,
2013.
(1) Within 12 months after the effective
date of this AD, install integrated display
system software.
(2) Within 60 months after the effective
date of this AD, replace the duct assembly
with a new duct assembly, do wiring
changes, and route certain wire bundles.
(k) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Alert
Service Bulletin 747–21A2523, Revision 1,
dated October 3, 2011, which was
incorporated by reference in AD 2012–24–10,
Amendment 39–17280 (77 FR 73908,
December 12, 2012).
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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
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57085
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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
required by this AD if it is approved by
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2012–24–10,
Amendment 39–17280 (77 FR 73908,
December 12, 2012), are approved as AMOCs
for the corresponding provisions of
paragraphs (g) and (h) of this AD.
(m) Related Information
(1) For more information about this AD,
contact Francis Smith, Aerospace Engineer,
Cabin Safety and Environmental Systems
Branch, ANM–150S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue
SW., Renton, WA 98057–3356; phone: 425–
917–6596; fax: 425–917–6591; email:
Francis.Smith@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) 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 747–
21A2523, Revision 2, dated June 7, 2013.
(ii) Boeing Special Attention Service
Bulletin 747–21–2532, dated February 13,
2014.
(iii) Boeing Special Attention Service
Bulletin 747–21–2533, dated February 13,
2014.
(3) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2H–65, Seattle, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at FAA, Transport Airplane Directorate, 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
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Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
September 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–23539 Filed 9–21–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0753; Directorate
Identifier 2014–NM–128–AD; Amendment
39–18270; AD 2015–19–08]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2011–19–
04, for all Airbus Model A318, A319,
A320, and A321 series airplanes. AD
2011–19–04 required repetitive
inspections for cracking of the left-hand
and right-hand inboard and outboard
elevator servo-control rod eye-ends, and
corrective actions if necessary. This new
AD requires an inspection to determine
if certain elevator servo-control parts are
installed, and replacement if necessary.
This AD was prompted by a
determination that certain elevator
servo-control parts that do not conform
to the approved type design have been
installed and may have the potential of
cracks in the rod eye-end. We are
issuing this AD to detect and correct rod
eye-end cracking, which could result in
uncontrolled elevator surface and
consequent reduced control of the
airplane.
SUMMARY:
This AD becomes effective
October 27, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 27, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of October 21, 2011 (76 FR
57630, September 16, 2011).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
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DATES:
VerDate Sep<11>2014
13:50 Sep 21, 2015
Jkt 235001
this AD as of September 22, 2009 (74 FR
41611 August 18, 2009).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0753; or in
person at the Docket 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.
For Airbus service information
identified in this AD, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. For
UTC service information identified in
this AD, contact UTC Aerospace
Systems; Roger Dangremont; telephone
+01 34 32 63 28; email
roger.dangrement@goodrich.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0753.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011). AD 2011–19–04
applied to all Model A318, A319, A320,
and A321 series airplanes. The NPRM
published in the Federal Register on
October 21, 2014 (79 FR 62928). The
NPRM was prompted by a
determination that certain elevator
servo-control parts that do not conform
to the approved type design have been
installed and may have the potential of
cracks in the rod eye-end. The NPRM
proposed to continue to require
repetitive inspections of the left-hand
and right-hand inboard and outboard
elevator servo-control rod eye-ends for
cracking, and corrective actions if
necessary. The NPRM also proposed to
require an inspection to determine if
certain elevator servo-control parts are
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installed, and replacement if necessary.
We are issuing this AD to detect and
correct rod eye-end cracking, which
could result in uncontrolled elevator
surface and consequent reduced control
of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0137, dated May 28,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition. The MCAI states:
One case of elevator servo-control
disconnection was reported on an A320
family aeroplane. Investigation results
revealed that the failure occurred at the
servo-control rod eye-end. Prompted by this
finding, additional inspections revealed
cracking at the same location on a number of
other servo-control rod eye-ends. In several
cases, both actuators of the same elevator
surface were affected.
It was determined that the detected rod
end cracks are caused by fatigue, induced by
a bending effect which is linked to the
spherical bearing rotational torque. As the
elevator surface is neither actuated nor
damped, a dual servo-control disconnection
on the same elevator would result in an
uncontrolled surface.
This condition, if not corrected, could
result in reduced control of the aeroplane.
To address this potential unsafe condition,
EASA issued [an airworthiness directive
(later revised)] [which corresponds to FAA
AD 2009–17–04, Amendment 39–15995 (74
FR 41611, August 18, 2009)] to require a onetime inspection of the elevator servo-control
rod eye-ends for aeroplanes which had
accumulated more than 10,000 flight cycles
(FC) since aeroplane first flight and, in case
of findings, accomplishment of corrective
actions.
As a result of EASA AD 2008–0149, a
significant number of rod eye-ends were
found cracked. In addition, some cracks were
reported on rod eye-ends that had not yet
accumulated the 10,000 FC of the established
threshold.
Prompted by these findings, EASA issued
[an airworthiness directive (later revised)]
[which corresponds to FAA AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011)], which partially
retained the initial inspection requirement of
EASA AD 2008–0149, which was
superseded, reduced the compliance time of
the initial inspection and introduced a
repetitive inspection programme.
After EASA AD 2010–0046R1 (https://
ad.easa.europa.eu/blob/easa_ad_2010_0046_
R1_superseded.pdf/AD_2010-0046R1_1) was
issued, a new elevator servo-control rod eyeend was developed, incorporating a regreasable roller bearing.
Consequently, EASA issued [EASA] AD
2013–0309 (later corrected) (https://
ad.easa.europa.eu/blob/easa_ad_2013_0309_
superseded.pdf/AD_2013-0309_1), retaining
the requirements of EASA AD 2010–0046R1,
which was superseded, and introduced an
E:\FR\FM\22SER1.SGM
22SER1
]]>Agencies
[Federal Register Volume 80, Number 183 (Tuesday, September 22, 2015)]
[Rules and Regulations]
[Pages 57083-57086]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-23539]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0245; Directorate Identifier 2014-NM-135-AD;
Amendment 39-18268; AD 2015-19-06]
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) 2012-24-10 for
certain The Boeing Company Model 747-400 and -400F series airplanes. AD
2012-24-10 required installing new software, replacing the duct
assembly with a new duct assembly, making wiring changes, and routing
certain wire bundles. This new AD retains the requirements of AD 2012-
24-10 and requires installing a new or serviceable pressure switch
bracket and altitude pressure switch. This new AD also adds an airplane
to the applicability. This AD was prompted by reports of intermittent
or blank displays of a certain integrated display unit (IDU) that were
due to an intermittent false electrical ground that was not addressed
by the software installation or wiring changes required by AD 2012-24-
10. We are issuing this AD to prevent IDU malfunctions, which could
affect the ability of the flightcrew to read primary displays for
airplane attitude, altitude, or airspeed, and consequently reduce the
ability of the flightcrew to maintain control of the airplane.
DATES: This AD is effective October 27, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 27,
2015.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0245.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.govby searching for and locating Docket No. FAA-2015-
0245; 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 Docket 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: Francis Smith, Aerospace Engineer,
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA
98057-3356; phone: 425-917-6596; fax: 425-917-6591; email:
Francis.Smith@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-24-10, Amendment 39-17280 (77 FR 73908,
December 12, 2012). AD 2012-24-10 applied to certain The Boeing Company
Model 747-400 and -400F series airplanes. The NPRM published in the
Federal Register on February 18, 2015 (80 FR 8568). The NPRM was
prompted by reports of intermittent or blank displays of a certain IDU
that were due to an intermittent false electrical ground that was not
addressed by the software installation or wiring changes required by AD
2012-24-10.
The NPRM (80 FR 8568, February 18, 2015) proposed to retain the
requirements of AD 2012-24-10. The NPRM also proposed to require
installing a new or serviceable pressure switch bracket and altitude
pressure switch, and add an airplane having variable number RT061 as
Group 21 to the applicability of the existing AD. We are issuing this
AD to prevent IDU malfunctions, which could affect the ability of the
flightcrew to read primary displays for airplane attitude, altitude, or
airspeed, and consequently reduce the ability of the flightcrew to
maintain control of the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM (80 FR
8568, February 18, 2015) and the FAA's response.
Request To Clarify Purpose of Altitude Pressure Switch
Boeing requested that we revise the wording in the Discussion
section to clarify that the altitude pressure switch provides an
independent and redundant signal to the equipment cooling three-way
valve. Boeing explained that the logic to transition the three-way
valve through an altitude of 25,000 feet was already present through a
signal from the environmental control system miscellaneous card
(ECSMC). The commenter added that the logic
[[Page 57084]]
redundancy is described correctly elsewhere in the NPRM (80 FR 8568,
February 18, 2015).
We agree with the commenter's request because changing the wording
clarifies the intent of Boeing Special Attention Service Bulletin 747-
21-2533, dated February 13, 2014, which describes procedures for
installing an altitude pressure switch on the forward side of the
station 400 bulkhead for the three-way valve of the equipment cooling
system. We have revised the description of the service information,
which is provided in the Related Service Information under 1 CFR part
51 section in this final rule.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (80 FR 8568, February 18, 2015) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 8568, February 18, 2015).
Related Service Information Under 1 CFR Part 51
Boeing has issued the following service information.
Boeing Alert Service Bulletin 747-21A2523, Revision 2,
dated June 7, 2013. This service information describes procedures for
changing the wiring and operating logic of the equipment cooling three-
way valve and replacing the existing duct assembly with a new duct
assembly on the main distribution manifold of the air conditioning
system.
Boeing Special Attention Service Bulletin 747-21-2532,
dated February 13, 2014. This service information describes procedures
for installing an altitude pressure switch on the forward side of the
station 400 bulkhead for the three-way valve of the equipment cooling
system.
Boeing Special Attention Service Bulletin 747-21-2533,
dated February 13, 2014. This service information describes procedures
for adding a second altitude signal to the switching logic for the
three-way valve to provide a second, independent altitude signal for
the equipment cooling system.
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 of this
AD.
Costs of Compliance
We estimate that this AD affects 33 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Duct assembly and replacement wiring 44 work-hours x $85 per hour $20,121 $23,861 $787,413
changes (retained actions from AD 2012- = $3,740.
24-10, Amendment 39-17280 (77 FR 73908,
December 12, 2012).
Software changes (retained actions from 3 work-hours x $85 per hour 0 255 8,415
AD 2012-24-10, Amendment 39-17280 (77 = $255.
FR 73908, December 12, 2012).
Altitude pressure switch installation 13 work-hours x $85 per hour 5,230 6,335 209,055
(new action). = $1,105.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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
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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2012-24-10, Amendment 39-17280 (77 FR 73908, December 12, 2012), and
adding the following new AD:
2015-19-06 The Boeing Company: Amendment 39-18268; Docket No. FAA-
2015-0245; Directorate Identifier 2014-NM-135-AD.
[[Page 57085]]
(a) Effective Date
This AD is effective October 27, 2015.
(b) Affected ADs
This AD replaces AD 2012-24-10, Amendment 39-17280 (77 FR 73908,
December 12, 2012).
(c) Applicability
This AD applies to The Boeing Company Model 747-400 and -400F
series airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin 747-21A2523, Revision 2, dated June 7,
2013.
(d) Subject
Air Transport Association (ATA) of America Code 21, Air
Conditioning; 31, Instruments.
(e) Unsafe Condition
This AD was prompted by reports of intermittent or blank
displays of a certain integrated display unit (IDU) in the flight
deck. We are issuing this AD to prevent IDU malfunctions, which
could affect the ability of the flightcrew to read primary displays
for airplane attitude, altitude, or airspeed, and consequently
reduce the ability of the flightcrew to maintain control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Software Update, With Revised Service Information
This paragraph restates the requirements of paragraph (g) of AD
2012-24-10, Amendment 39-17280 (77 FR 73908, December 12, 2012),
with revised service information. Within 12 months after January 16,
2013 (the effective date of AD 2012-24-10), except as provided by
paragraph (j) of this AD: Install integrated display system
software, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-21A2523, Revision 1, dated October
3, 2011; or Boeing Alert Service Bulletin 747-21A2523, Revision 2,
dated June 7, 2013. As of the effective date of this AD, only Boeing
Alert Service Bulletin 747-21A2523, Revision 2, dated June 7, 2013,
may be used to accomplish the actions required by this paragraph.
Note 1 to paragraphs (g) and (j) of this AD: Boeing Alert
Service Bulletin 747-21A2523, Revision 1, dated October 3, 2011; and
Boeing Alert Service Bulletin 747-21A2523, Revision 2, dated June 7,
2013; refer to Boeing Service Bulletin 747-31-2426, dated July 29,
2010 (for airplanes with Rolls-Royce engines); Boeing Service
Bulletin 747-31-2427, dated July 29, 2010 (for airplanes with
General Electric engines); and Boeing Service Bulletin 747-31-2428,
dated July 29, 2010 (for airplanes with Pratt & Whitney engines); as
additional sources of guidance for the software installation
specified by paragraph (g) of this AD.
(h) Retained Duct Assembly Replacement and Wiring Changes, With Revised
Service Information
This paragraph restates the requirements of paragraph (h) of AD
2012-24-10, Amendment 39-17280 (77 FR 73908, December 12, 2012),
with revised service information. Within 60 months after January 16,
2013 (the effective date of AD 2012-24-10), except as provided by
paragraph (j) of this AD: Replace the duct assembly with a new duct
assembly, do wiring changes, and route certain wire bundles, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-21A2523, Revision 1, dated October 3, 2011; or
Boeing Alert Service Bulletin 747-21A2523, Revision 2, dated June 7,
2013. As of the effective date of this AD, only Boeing Alert Service
Bulletin 747-21A2523, Revision 2, dated June 7, 2013, may be used to
accomplish the actions required by this paragraph.
(i) New Installation of Pressure Switch Bracket and Altitude Pressure
Switch
Within 60 months after the effective date of this AD: Install a
new or serviceable pressure switch bracket and a new or serviceable
altitude pressure switch on the forward side of the station 400
bulkhead, do wiring changes, route certain wire bundles, install a
new hose assembly, and perform a leak check and a functional logic
test, in accordance with the Accomplishment Instructions of the
service information specified in paragraph (i)(1) or (i)(2) of this
AD, as applicable.
(1) For Model 747-400F series airplanes: Boeing Special
Attention Service Bulletin 747-21-2532, dated February 13, 2014.
(2) For Model 747-400BCF series airplanes: Boeing Special
Attention Service Bulletin 747-21-2533, dated February 13, 2014.
(j) Actions for Group 21 Airplanes
For Group 21 airplanes, as identified in Boeing Alert Service
Bulletin 747-21A2523, Revision 2, dated June 7, 2013, do the actions
specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-21A2523, Revision 2, dated June 7, 2013.
(1) Within 12 months after the effective date of this AD,
install integrated display system software.
(2) Within 60 months after the effective date of this AD,
replace the duct assembly with a new duct assembly, do wiring
changes, and route certain wire bundles.
(k) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Boeing Alert Service
Bulletin 747-21A2523, Revision 1, dated October 3, 2011, which was
incorporated by reference in AD 2012-24-10, Amendment 39-17280 (77
FR 73908, December 12, 2012).
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
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 ACO, send it to the
attention of the person identified in paragraph (m)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-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 required by this AD if it is approved by Boeing
Commercial Airplanes Organization Designation Authorization (ODA)
that has been authorized by the Manager, Seattle ACO, to make those
findings. For a repair method to be approved, the repair must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved for AD 2012-24-10, Amendment 39-17280 (77 FR
73908, December 12, 2012), are approved as AMOCs for the
corresponding provisions of paragraphs (g) and (h) of this AD.
(m) Related Information
(1) For more information about this AD, contact Francis Smith,
Aerospace Engineer, Cabin Safety and Environmental Systems Branch,
ANM-150S, FAA, Seattle Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6596; fax:
425-917-6591; email: Francis.Smith@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) 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 747-21A2523, Revision 2, dated
June 7, 2013.
(ii) Boeing Special Attention Service Bulletin 747-21-2532,
dated February 13, 2014.
(iii) Boeing Special Attention Service Bulletin 747-21-2533,
dated February 13, 2014.
(3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet
https://www.myboeingfleet.com.
(4) You may view this service information at FAA, Transport
Airplane Directorate, 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
[[Page 57086]]
the availability of this material at NARA, call 202-741-6030, or go
to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-23539 Filed 9-21-15; 8:45 am]
BILLING CODE 4910-13-P
