Airworthiness Directives; The Boeing Company Airplanes, 73805-73808 [2014-28916]
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Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations
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originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as a need to
incorporate new revisions into the aircraft
maintenance manual (AMM) or in the
Limitations document of the FAA-approved
maintenance program. The limitations were
revised to incorporate new life limits for the
fire extinguisher. These actions are required
to ensure the continued operational safety of
the affected airplanes.
(f) Actions and Compliance
(1) Actions retained from AD 2013–11–08,
Amendment 39–17468 (78 FR 37701; June 24,
2013) for all airplanes in the Applicability
section of this AD: If the flap actuator has
accumulated 3,500 hours time-in-service
(TIS) or more since new or last overhauled
or 7 years or more since new or last
overhauled, whichever occurs first,
replacement of the flap actuator (except part
numbers 978.73.14.101 and 978.73.14.103) is
required within 350 hours TIS after July 29,
2013, (the effective date retained from AD
2013–11–08) or 6 months after July 29, 2013,
(the effective date retained from AD 2013–
11–08), whichever occurs first. Flap actuators
with less than 3,500 hours TIS or 7 years
since new or last overhauled are covered by
the airworthiness limitations document
(ALS) requirement.
(2) Actions new to this AD for all affected
Models PC–6/B2–H2 and PC–6/B2–H4
airplanes: Before further flight after January
16, 2015 (the effective date of this AD)
incorporate the maintenance requirements as
specified in Section 04–00–00, Airworthiness
Limitations, of Chapter 04, Airworthiness
Limitations, of the Pilatus PC–6 Maintenance
Manual, document number 01975, Revision
19, dated May 31, 2014, into your FAAaccepted maintenance program (maintenance
manual).
(3) Actions new to this AD for all airplanes
in the Applicability section of this AD except
for the Models PC–6/B2–H2 and PC–6/B2–H4
airplanes: Before further flight after January
16, 2015 (the effective date of this AD)
incorporate the maintenance requirements as
specified in Pilatus ALS, document number
02334, Revision 4, dated May 31, 2014, into
your FAA-accepted maintenance program
(maintenance manual).
(4) Actions new to this AD for all airplanes
in the Applicability section of this AD:
(i) For airplanes with Halon Fire
Extinguishers that have not yet reached the
10 year life limit after January 16, 2015 (the
effective date of this AD), when the Halon
Fire Extinguisher reaches its life limit of 10
years, before further flight, replace with an
airworthy Halon Fire Extinguisher following
Section 04–00–00, Airworthiness
Limitations, of Chapter 04, Airworthiness
Limitations, of the Pilatus PC–6 Maintenance
Manual, document number 01975, Revision
19, dated May 31, 2014; or Pilatus ALS
document number 02334, Revision 4, dated
May 31, 2014; as applicable.
(ii) For airplanes with Halon Fire
Extinguishers that have reached the 10 year
life limit on or before January 16, 2015 (the
effective date of this AD), within the next 6
months after January 16, 2015 (the effective
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14:38 Dec 11, 2014
Jkt 235001
date of this AD), replace with an airworthy
Halon Fire Extinguisher following Section
04–00–00, Airworthiness Limitations, of
Chapter 04, Airworthiness Limitations, of the
Pilatus PC–6 Maintenance Manual, document
number 01975, Revision 19, dated May 31,
2014; or Pilatus ALS document number
02334, Revision 4, dated May 31, 2014; as
applicable.
(iii) Repetitively, after replacing the
airplanes Halon Fire Extinguisher as required
in paragraphs (f)(4)(i) or (f)(4)(ii), within 10
years after each last replacement, replace
with an airworthy Halon Fire Extinguisher.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; fax: (816) 329–
4090; email: doug.rudolph@faa.gov. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(h) Related Information
Refer to European Aviation Safety Agency
(EASA) AD No.: 2014–0181, dated July 31,
2014, for related information. The MCAI can
be found in the AD docket on the Internet at:
https://www.regulations.gov/
#!docketDetail;D=FAA-2014-0717.
(i) 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) Pilatus Airworthiness Limitations
document number 02334, Revision 4, dated
May 31, 2014. The revision level of this
document is indicated only in the Record of
Revisions.
(ii) Section 04–00–00, Airworthiness
Limitations, of Chapter 04, Airworthiness
Limitations, of the Pilatus PC–6 Maintenance
Manual, document number 01975, Revision
19, dated May 31, 2014.
(3) For Pilatus Aircraft Limited service
information identified in this AD, contact
PILATUS AIRCRAFT LTD., Customer Liaison
Manager, CH–6371 STANS, Switzerland;
telephone: +41 (0) 41 619 65 80; fax: +41 (0)
41 619 65 76; Internet: https://www.pilatus-
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73805
aircraft.com; email: fodermatt@pilatusaircraft.com.
(4) You may view this service information
at FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Kansas City, Missouri, on
December 2, 2014.
Robert Busto,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–28730 Filed 12–11–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0053; Directorate
Identifier 2013–NM–174–AD; Amendment
39–18047; AD 2014–25–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 777
airplanes. This AD was prompted by
reports of corroded, migrated, or broken
spring pins of the girt bar floor fitting;
in one case the broken pins prevented
a door escape slide from deploying
during a maintenance test. This AD
requires replacing the existing spring
pins at each passenger entry door at
both girt bar floor fittings with new
spring pins. We are issuing this AD to
prevent broken or migrated spring pins
of the girt bar floor fittings, which could
result in improper deployment of the
escape slide/raft and consequent delay
and injury during evacuation of
passengers and crew from the cabin in
the event of an emergency.
DATES: This AD is effective January 16,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 16, 2015.
ADDRESSES: For service information
identified in this AD, contact Boeing
SUMMARY:
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Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations
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, Washington. For information on
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0053; 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: Ana
Martinez Hueto, 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: 425–917–6592;
fax: 425–917–6591; email:
ana.m.hueto@faa.gov.
SUPPLEMENTARY INFORMATION:
rljohnson on DSK3VPTVN1PROD with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 777 airplanes. The NPRM
published in the Federal Register on
February 6, 2014 (79 FR 7103). The
NPRM was prompted by reports of
corroded, migrated, or broken spring
pins of the girt bar floor fitting; in one
case the broken pins prevented a door
escape slide from deploying during a
maintenance test. The NPRM proposed
to require replacing the existing spring
pins at each passenger entry door at
both girt bar floor fittings with new
spring pins. We are issuing this AD to
prevent broken or migrated spring pins
of the girt bar floor fittings, which could
result in improper deployment of the
escape slide/raft and consequent delay
and injury during evacuation of
passengers and crew from the cabin in
the event of an emergency.
VerDate Sep<11>2014
14:38 Dec 11, 2014
Jkt 235001
Revised Service Information
Since publication of the NPRM (79 FR
7103, February 6, 2014), Boeing has
issued Service Bulletin 777–52A0050,
Revision 1, dated August 7, 2014. That
revision states that no more work is
necessary on airplanes changed in
accordance with the original issue
(Boeing Alert Service Bulletin 777–
52A0050, dated June 18, 2013), which
was specified as the appropriate source
of service information in the NPRM.
We have changed paragraphs (c) and
(g) of this AD to specify Boeing Service
Bulletin 777–52A0050, Revision 1,
dated August 7, 2014; added a new
paragraph (h) to this AD to give credit
for actions done before the effective date
of this AD using Boeing Alert Service
Bulletin 777–52A0050, dated June 18,
2013; and redesignated subsequent
paragraphs accordingly.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 7103,
February 6, 2014) and the FAA’s
response to each comment.
Request To Change Compliance Time
Boeing asked that we change the
compliance time in paragraph (g) of the
NPRM (79 FR 7103, February 6, 2014)
from 36 months to 1,175 days. Boeing
stated that 1,175 days (3 years, 80 days)
is consistent with the compliance time
specified in Boeing Alert Service
Bulletin 777–52A0050, dated June 18,
2013. Boeing noted that this compliance
time encompasses the 777 maintenance
planning document C-check inspection
interval of 1,125 days (3 years, 30 days)
for structural items. Boeing added that
this change is not significant.
American Airlines (AA) asked that we
change the compliance time to match
the Maintenance Review Board (MRB)
limit of 1,125 days, which would allow
AA’s maintenance to be scheduled at
regular maintenance visits without any
undue burden on current flight
schedules.
We agree with changing the
compliance time to coincide with
regular maintenance inspection
intervals. However, instead of
specifying 1,175 days, we worked in
conjunction with Boeing to determine
that a 37-month compliance time is
appropriate. We have changed
paragraph (g) of this AD accordingly.
Request To Limit Parts Installation
Prohibition
Delta Airlines (Delta) asked that we
revise paragraph (h) of the NPRM (79 FR
7103, February 6, 2014), which is
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Fmt 4700
Sfmt 4700
paragraph (i) of this AD, to prohibit
installation of the specified spring pins
only in the locations being addressed by
this AD. Delta stated that this
clarification would allow the use of part
number (P/N) MS39086–261 or P/N
MS16562–252 in locations not subject to
the actions in the NPRM. Delta added
that the proposed language would
prevent the use of these pins anywhere
on the applicable Model 777 airplanes.
We agree to specify the location on
the airplane where installation of the
spring pins is prohibited. We have
changed paragraph (i) of this AD
accordingly.
Request To Revise Parts Installation
Prohibition to Pertain to Unmodified
Airplanes Only
AA asked that we prohibit installation
of spring pins only on airplanes
modified in accordance with Boeing
Service Bulletin 777–52A0050, Revision
1, dated August 7, 2014, and allow
installation of the spring pins on
unmodified airplanes. AA added that
the Boeing Model 777 Illustrated Parts
Catalog (IPC) currently identifies spring
pins having P/N MS16562–252 as valid
parts for installation on unmodified
airplanes. AA added that, since the
analysis of broken spring pins has
shown that they have failed due to
stress corrosion, it should be acceptable
to install a new pin in an unmodified
airplane because the airplane will be
modified within a set amount of time.
We do not agree to allow installation
of the spring pins having part number
MS39086–261 or MS16562–252 on
unmodified airplanes. In general, once
we have determined that an unsafe
condition exists, we do not allow that
condition to be introduced into the fleet.
In developing the technical information
on which every AD is based, we
consider the availability of replacement
parts that the AD will require to be
installed. Since we have determined
that replacement parts are available to
operators, this AD prohibits installation
of the unsafe parts. We have not
changed this AD in this regard.
Request To Define Configuration/Parts
Control
Singapore Airlines asked for an
explanation of how Boeing ensures that
the affected spring pins are not
delivered to operators since the girt bar
assembly includes the spring pins.
FedEx asked that we revise the NPRM
(79 FR 7103, February 6, 2014) either to
specifically state that no reidentification
of the floor fitting assemblies is
required, or to provide a specific
reidentification process. FedEx Express
also asked that the issue of parts
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Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations
identification as specified in the
referenced service information (Boeing
Alert Service Bulletin 777–52A0050,
dated June 18, 2013), be resolved. FedEx
noted ‘‘a vague requirement’’ to identify
accomplishment of the service bulletin
on the part but there are no specific
instructions. FedEx stated this could
result in the part being inadvertently
returned to a pre-modification
condition. FedEx recognized that
ensuring compliance lies in the control
of the spring pins, not the floor fitting
assemblies. FedEx stated that there is no
value added by identifying the part after
the change is made because Boeing did
not provide a step in the Work
Instructions with a location to apply
this identification.
We acknowledge the commenter’s
concerns. Since issuance of the NPRM
(79 FR 7103, February 6, 2014), Boeing
has updated its IPC and Boeing Service
Bulletin 777–52A0050, Revision 1,
dated August 7, 2014, to clarify
appropriate parts installation. In
addition, Boeing Service Bulletin 777–
determined that air safety and the
public interest require adopting this AD
with the changes described previously,
except for minor editorial changes. We
have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR 7103,
February 6, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 7103,
February 6, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
52A0050, Revision 1, dated August 7,
2014, includes Work Instructions for
applying the part identification. We
have not changed this AD in this regard.
Concern Regarding Parts Availability
FedEx expressed concern about the
ability of operators to obtain the
required parts since Boeing currently
restricts the part’s availability. FedEx
noted that it has an adequate supply.
We consider the compliance times in
this AD to be adequate to allow
operators to acquire parts to have on
hand for replacing the affected spring
pins. Therefore, we have determined
that, due to the safety implications and
consequences associated with corroded,
migrated, or broken spring pins, the
existing pins must be replaced within
37 months after the effective date of this
AD. We have not changed this AD
regarding this issue.
Costs of Compliance
We estimate that this AD affects 189
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
Conclusion
We reviewed the relevant data,
considered the comments received, and
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Replacement .................
Up to 40 work-hours × $85 per hour = Up to
$3,400.
$0
Up to $3,400 ........................
rljohnson on DSK3VPTVN1PROD with RULES
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.
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.
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
Adoption of the Amendment
VerDate Sep<11>2014
14:38 Dec 11, 2014
Jkt 235001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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Frm 00007
Fmt 4700
Sfmt 4700
Cost on U.S.
operators
Up to $642,600.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2014–25–05 The Boeing Company:
Amendment 39–18047 ; Docket No.
FAA–2014–0053; Directorate Identifier
2013–NM–174–AD.
(a) Effective Date
This AD is effective January 16, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 777–200, –200LR, –300, –300ER, and
777F series airplanes, certificated in any
category, as identified in Boeing Service
Bulletin 777–52A0050, Revision 1, dated
August 7, 2014.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
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Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations
(e) Unsafe Condition
This AD was prompted by reports of
corroded, migrated, or broken spring pins of
the girt bar floor fitting; in one case the
broken pins prevented a door escape slide
from deploying during a maintenance test.
We are issuing this AD to prevent broken or
migrated spring pins of the girt bar floor
fittings, which could result in improper
deployment of the escape slide/raft and
consequent delay and injury during
evacuation of passengers and crew from the
cabin in the event of an emergency.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Spring Pin Replacement
Within 37 months after the effective date
of this AD: Replace the spring pin at both girt
bar floor fittings at each passenger entry door
with a new spring pin, in accordance with
the Accomplishment Instructions of Boeing
Service Bulletin 777–52A0050, Revision 1,
dated August 7, 2014.
(h) Credit for Previous Actions
This paragraph provides credit for the
action specified in paragraph (g) of this AD,
if that action was performed before the
effective date of this AD using Boeing Alert
Service Bulletin 777–52A0050, dated June
18, 2013, which is not incorporated by
reference in this AD.
rljohnson on DSK3VPTVN1PROD with RULES
(i) Parts Installation Prohibition
As of the effective date of this AD, no
person may install a spring pin having part
number MS39086–261 or MS16562–252 at a
girt bar floor fitting at a passenger entry door
on any airplane.
Engineer, Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6592; fax: 425–917–6591;
email: ana.m.hueto@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses in paragraphs (l)(3)
and (l)(4) of this AD.
(l) 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 Service Bulletin 777–52A0050,
Revision 1, dated August 7, 2014.
(ii) Reserved.
(3) 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.
(4) You may view this 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
(j) 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 (k)(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 the
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.
Issued in Renton, WA, on November 28,
2014.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
(k) Related Information
(1) For more information about this AD,
contact Ana Martinez Hueto, Aerospace
SUMMARY:
VerDate Sep<11>2014
14:38 Dec 11, 2014
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[FR Doc. 2014–28916 Filed 12–11–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–1029; Directorate
Identifier 2013–NM–177–AD; Amendment
39–18042; AD 2014–25–01]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2010–13–
04 for certain Bombardier, Inc. Model
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Sfmt 4700
DHC–8–400 series airplanes. AD 2010–
13–04 required modifying the nose
landing gear (NLG) trailing arm. This
new AD requires installing a new pivot
pin retention mechanism. This new AD
also adds airplanes to the applicability.
This AD was prompted by a report of
several missing or damaged pivot pin
retention bolts. We are issuing this AD
to prevent failure of the pivot pin
retention bolt, which could result in a
loss of directional control or loss of a
NLG tire during take-off or landing.
DATES: This AD becomes effective
January 16, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 16, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of July 28, 2010 (75 FR
35622, June 23, 2010).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-1029; 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 service information identified in
this AD, contact Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5,
Canada; telephone 416–375–4000; fax
416–375–4539; email thd.qseries@
aero.bombardier.com; Internet https://
www.bombardier.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.
FOR FURTHER INFORMATION CONTACT:
Ricardo Garcia, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7331; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010–13–04,
Amendment 39–16335 (75 FR 35622,
June 23, 2010). AD 2010–13–04 applied
to certain Bombardier, Inc. Model DHC–
8–400 series airplanes. The NPRM
published in the Federal Register on
December 24, 2013 (78 FR 77615).
E:\FR\FM\12DER1.SGM
12DER1
Agencies
[Federal Register Volume 79, Number 239 (Friday, December 12, 2014)]
[Rules and Regulations]
[Pages 73805-73808]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-28916]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0053; Directorate Identifier 2013-NM-174-AD;
Amendment 39-18047; AD 2014-25-05]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 777 airplanes. This AD was prompted by reports
of corroded, migrated, or broken spring pins of the girt bar floor
fitting; in one case the broken pins prevented a door escape slide from
deploying during a maintenance test. This AD requires replacing the
existing spring pins at each passenger entry door at both girt bar
floor fittings with new spring pins. We are issuing this AD to prevent
broken or migrated spring pins of the girt bar floor fittings, which
could result in improper deployment of the escape slide/raft and
consequent delay and injury during evacuation of passengers and crew
from the cabin in the event of an emergency.
DATES: This AD is effective January 16, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 16,
2015.
ADDRESSES: For service information identified in this AD, contact
Boeing
[[Page 73806]]
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, Washington. For
information on the availability of this material at the FAA, call 425-
227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0053; 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: Ana Martinez Hueto, 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: 425-917-6592; fax: 425-917-6591; email:
ana.m.hueto@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain The Boeing Company
Model 777 airplanes. The NPRM published in the Federal Register on
February 6, 2014 (79 FR 7103). The NPRM was prompted by reports of
corroded, migrated, or broken spring pins of the girt bar floor
fitting; in one case the broken pins prevented a door escape slide from
deploying during a maintenance test. The NPRM proposed to require
replacing the existing spring pins at each passenger entry door at both
girt bar floor fittings with new spring pins. We are issuing this AD to
prevent broken or migrated spring pins of the girt bar floor fittings,
which could result in improper deployment of the escape slide/raft and
consequent delay and injury during evacuation of passengers and crew
from the cabin in the event of an emergency.
Revised Service Information
Since publication of the NPRM (79 FR 7103, February 6, 2014),
Boeing has issued Service Bulletin 777-52A0050, Revision 1, dated
August 7, 2014. That revision states that no more work is necessary on
airplanes changed in accordance with the original issue (Boeing Alert
Service Bulletin 777-52A0050, dated June 18, 2013), which was specified
as the appropriate source of service information in the NPRM.
We have changed paragraphs (c) and (g) of this AD to specify Boeing
Service Bulletin 777-52A0050, Revision 1, dated August 7, 2014; added a
new paragraph (h) to this AD to give credit for actions done before the
effective date of this AD using Boeing Alert Service Bulletin 777-
52A0050, dated June 18, 2013; and redesignated subsequent paragraphs
accordingly.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 7103, February 6, 2014) and the FAA's response to each comment.
Request To Change Compliance Time
Boeing asked that we change the compliance time in paragraph (g) of
the NPRM (79 FR 7103, February 6, 2014) from 36 months to 1,175 days.
Boeing stated that 1,175 days (3 years, 80 days) is consistent with the
compliance time specified in Boeing Alert Service Bulletin 777-52A0050,
dated June 18, 2013. Boeing noted that this compliance time encompasses
the 777 maintenance planning document C-check inspection interval of
1,125 days (3 years, 30 days) for structural items. Boeing added that
this change is not significant.
American Airlines (AA) asked that we change the compliance time to
match the Maintenance Review Board (MRB) limit of 1,125 days, which
would allow AA's maintenance to be scheduled at regular maintenance
visits without any undue burden on current flight schedules.
We agree with changing the compliance time to coincide with regular
maintenance inspection intervals. However, instead of specifying 1,175
days, we worked in conjunction with Boeing to determine that a 37-month
compliance time is appropriate. We have changed paragraph (g) of this
AD accordingly.
Request To Limit Parts Installation Prohibition
Delta Airlines (Delta) asked that we revise paragraph (h) of the
NPRM (79 FR 7103, February 6, 2014), which is paragraph (i) of this AD,
to prohibit installation of the specified spring pins only in the
locations being addressed by this AD. Delta stated that this
clarification would allow the use of part number (P/N) MS39086-261 or
P/N MS16562-252 in locations not subject to the actions in the NPRM.
Delta added that the proposed language would prevent the use of these
pins anywhere on the applicable Model 777 airplanes.
We agree to specify the location on the airplane where installation
of the spring pins is prohibited. We have changed paragraph (i) of this
AD accordingly.
Request To Revise Parts Installation Prohibition to Pertain to
Unmodified Airplanes Only
AA asked that we prohibit installation of spring pins only on
airplanes modified in accordance with Boeing Service Bulletin 777-
52A0050, Revision 1, dated August 7, 2014, and allow installation of
the spring pins on unmodified airplanes. AA added that the Boeing Model
777 Illustrated Parts Catalog (IPC) currently identifies spring pins
having P/N MS16562-252 as valid parts for installation on unmodified
airplanes. AA added that, since the analysis of broken spring pins has
shown that they have failed due to stress corrosion, it should be
acceptable to install a new pin in an unmodified airplane because the
airplane will be modified within a set amount of time.
We do not agree to allow installation of the spring pins having
part number MS39086-261 or MS16562-252 on unmodified airplanes. In
general, once we have determined that an unsafe condition exists, we do
not allow that condition to be introduced into the fleet. In developing
the technical information on which every AD is based, we consider the
availability of replacement parts that the AD will require to be
installed. Since we have determined that replacement parts are
available to operators, this AD prohibits installation of the unsafe
parts. We have not changed this AD in this regard.
Request To Define Configuration/Parts Control
Singapore Airlines asked for an explanation of how Boeing ensures
that the affected spring pins are not delivered to operators since the
girt bar assembly includes the spring pins.
FedEx asked that we revise the NPRM (79 FR 7103, February 6, 2014)
either to specifically state that no reidentification of the floor
fitting assemblies is required, or to provide a specific
reidentification process. FedEx Express also asked that the issue of
parts
[[Page 73807]]
identification as specified in the referenced service information
(Boeing Alert Service Bulletin 777-52A0050, dated June 18, 2013), be
resolved. FedEx noted ``a vague requirement'' to identify
accomplishment of the service bulletin on the part but there are no
specific instructions. FedEx stated this could result in the part being
inadvertently returned to a pre-modification condition. FedEx
recognized that ensuring compliance lies in the control of the spring
pins, not the floor fitting assemblies. FedEx stated that there is no
value added by identifying the part after the change is made because
Boeing did not provide a step in the Work Instructions with a location
to apply this identification.
We acknowledge the commenter's concerns. Since issuance of the NPRM
(79 FR 7103, February 6, 2014), Boeing has updated its IPC and Boeing
Service Bulletin 777-52A0050, Revision 1, dated August 7, 2014, to
clarify appropriate parts installation. In addition, Boeing Service
Bulletin 777-52A0050, Revision 1, dated August 7, 2014, includes Work
Instructions for applying the part identification. We have not changed
this AD in this regard.
Concern Regarding Parts Availability
FedEx expressed concern about the ability of operators to obtain
the required parts since Boeing currently restricts the part's
availability. FedEx noted that it has an adequate supply.
We consider the compliance times in this AD to be adequate to allow
operators to acquire parts to have on hand for replacing the affected
spring pins. Therefore, we have determined that, due to the safety
implications and consequences associated with corroded, migrated, or
broken spring pins, the existing pins must be replaced within 37 months
after the effective date of this AD. We have not changed this AD
regarding this issue.
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, except for minor
editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 7103, February 6, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 7103, February 6, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 189 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Replacement................... Up to 40 work-hours x $0 Up to $3,400.... Up to $642,600.
$85 per hour = Up to
$3,400.
----------------------------------------------------------------------------------------------------------------
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
(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 adding the following new airworthiness
directive (AD):
2014-25-05 The Boeing Company: Amendment 39-18047 ; Docket No. FAA-
2014-0053; Directorate Identifier 2013-NM-174-AD.
(a) Effective Date
This AD is effective January 16, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes, certificated in any
category, as identified in Boeing Service Bulletin 777-52A0050,
Revision 1, dated August 7, 2014.
(d) Subject
Air Transport Association (ATA) of America Code 52, Doors.
[[Page 73808]]
(e) Unsafe Condition
This AD was prompted by reports of corroded, migrated, or broken
spring pins of the girt bar floor fitting; in one case the broken
pins prevented a door escape slide from deploying during a
maintenance test. We are issuing this AD to prevent broken or
migrated spring pins of the girt bar floor fittings, which could
result in improper deployment of the escape slide/raft and
consequent delay and injury during evacuation of passengers and crew
from the cabin in the event of an emergency.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Spring Pin Replacement
Within 37 months after the effective date of this AD: Replace
the spring pin at both girt bar floor fittings at each passenger
entry door with a new spring pin, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 777-52A0050,
Revision 1, dated August 7, 2014.
(h) Credit for Previous Actions
This paragraph provides credit for the action specified in
paragraph (g) of this AD, if that action was performed before the
effective date of this AD using Boeing Alert Service Bulletin 777-
52A0050, dated June 18, 2013, which is not incorporated by reference
in this AD.
(i) Parts Installation Prohibition
As of the effective date of this AD, no person may install a
spring pin having part number MS39086-261 or MS16562-252 at a girt
bar floor fitting at a passenger entry door on any airplane.
(j) 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 (k)(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 the
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.
(k) Related Information
(1) For more information about this AD, contact Ana Martinez
Hueto, 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: 425-917-6592;
fax: 425-917-6591; email: ana.m.hueto@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses in
paragraphs (l)(3) and (l)(4) of this AD.
(l) 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 Service Bulletin 777-52A0050, Revision 1, dated
August 7, 2014.
(ii) Reserved.
(3) 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.
(4) You may view this 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, WA, on November 28, 2014.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-28916 Filed 12-11-14; 8:45 am]
BILLING CODE 4910-13-P