Airworthiness Directives; The Boeing Company Airplanes, 41894-41897 [2016-14966]
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41894
Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA Design Organization
Approval (DOA).
(e) Reason
This AD was prompted by a report
indicating that during inspections to detect
corrosion of the bulk cargo doors, several
cracks were discovered. We are issuing this
AD to detect and correct cracking of the bulk
cargo doors; such cracking could result in
rapid airplane decompression or possible
loss of the bulk cargo door.
(k) Other FAA AD Provisions
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection
Within 250 flight cycles or 6 months after
the effective date of this AD, whichever
occurs first, do a general visual inspection of
the bulk cargo door frame to identify the
existence of any structural repairs, in
accordance with the instructions of Airbus
Alert Operators Transmission (AOT)
A53W010–15, Revision 00, including
Appendixes 1, 2, and 3, dated December 15,
2015.
(h) Detailed Visual Inspection
If, during the general visual inspection
required in paragraph (g) of this AD, any
repair is found on the bulk cargo door frame:
Before further flight, do a detailed visual
inspection for cracking of the frame at the
repaired area, in accordance with the
instructions of Airbus AOT A53W010–15,
Revision 00, including Appendixes 1, 2, and
3, dated December 15, 2015.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(i) Crack Repair
If any cracking is found during the detailed
visual inspection required by paragraph (h)
of this AD: Before further flight, repair using
a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA Design Organization
Approval (DOA).
(j) Post-Repair Actions for Crack-Free
Frames
If no cracking is found during the detailed
visual inspection required by paragraph (h)
of this AD: Do the actions in paragraphs (j)(1)
and (j)(2) of this AD.
(1) At the applicable time specified in
paragraph (j)(1)(i) or (j)(1)(ii) of this AD: Send
a report of the inspection results to Airbus
Service Bulletin Reporting Online
Application on Airbus World (https://
w3.airbus.com/).
(i) If the inspection was done on or after
the effective date of this AD: Submit the
report within 60 days after the inspection.
(ii) If the inspection was done before the
effective date of this AD: Submit the report
within 60 days after the effective date of this
AD.
(2) Within 2,800 flight cycles after the
detailed visual inspection required by
paragraph (h) of this AD: Do applicable postrepair inspections and repairs, using a
method approved by the Manager,
International Branch, ANM–116, Transport
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The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0238, dated
December 18, 2015, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–7269.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 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.
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.
Issued in Renton, Washington, on June 10,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–14968 Filed 6–27–16; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–7270; Directorate
Identifier 2015–NM–116–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–700
and –700C series airplanes. This
proposed AD was prompted by a report
that for airplanes with blended winglets,
the nose-up pitch trim limit and
associated warning for the horizontal
stabilizer control system will allow takeoff with incorrect trim settings. This
proposed AD would require, depending
on airplane configuration, replacing the
pitch trim light plates on the flight deck
control stand, relocating the position
warning horn switches of the horizontal
stabilizer, revising the software,
removing the placard, and doing related
investigative and corrective actions if
necessary. We are proposing this AD to
prevent take-off with incorrect settings
of the horizontal stabilizer pitch trim
system. Settings outside of the
appropriate pitch trim limits could
result in loss of controllability of the
airplane during take-off.
DATES: We must receive comments on
this proposed AD by August 12, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For Aviation Partners Boeing service
information identified in this NPRM,
contact Aviation Partners Boeing, 2811
South 102nd Street, Suite 200, Seattle,
WA 98168; phone: 206–830–7699; fax:
206–767–3355; email: leng@
aviationpartners.com; Internet: https://
www.aviationpartnersboeing.com.
SUMMARY:
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Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules
For The Boeing Company service
information identified in this NPRM,
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. Boeing Alert
Service Bulletin 737–27A1306, dated
September 10, 2015, is also available on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
7270.
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–2016–
7270; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Fnu
Winarto, Aerospace Engineer, Systems
and Equipment Branch, ANM–130S,
FAA, Seattle Aircraft Certification
Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–
917–6659; fax: 425–917–6590; email:
fnu.winarto@faa.gov.
SUPPLEMENTARY INFORMATION:
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2016–7270; Directorate Identifier 2015–
NM–116–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
41895
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
stabilizer trim system, and repairing the
light plate switch.
We reviewed Aviation Partners
Service Bulletin AP737–34–005, dated
July 17, 2015. The service information
describes procedures for revising the
software and removing the placard.
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.
Discussion
We have received a report that for
airplanes with blended winglets, the
nose-up pitch trim limit and associated
warning for the horizontal stabilizer
control system will allow takeoff with
incorrect trim settings. The trim control
system was recently analyzed for
potential nose-up mis-trim occurrences
during take-off for airplanes with
blended winglets. Results of the analysis
indicated that Model 737–700 airplanes
with blended winglets are not compliant
with the certification rules for specific
conditions. This condition, if not
corrected, could result in the loss of
controllability of the airplane during
take-off.
FAA’s Determination
Related Service Information Under 1
CFR Part 51
We reviewed Aviation Partners
Boeing Service Bulletin AP737–27–002,
Revision 2, dated March 1, 2016, and
Boeing Alert Service Bulletin 737–
27A1306, dated September 10, 2015.
The service information describes
procedures for replacing the pitch trim
light plates on the flight deck control
stand, relocating the position warning
horn switches of the horizontal
stabilizer, revising the software, and
doing related investigative and
corrective actions.
The related investigative actions
include verifying that the stabilizer ‘‘B’’
measurement is at a certain dimension,
performing a light plate function test,
performing a stabilizer functional test,
loading and verifying model/engine
database software, performing a flight
management computer configuration
check, and verifying all settings.
The corrective actions include
adjusting the stabilizer, adjusting the
light plate, replacing the light plate,
rigging and adjusting the horizontal
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Differences Between this Proposed AD
and the Service Information.’’ For
information on the procedures and
compliance times, see Boeing Alert
Service Bulletin 737–27A1306, dated
September 10, 2015, at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
7270.
Differences Between This Proposed AD
and the Service Information
The service information specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions in
one of the following ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) whom
we have authorized to make those
findings.
Costs of Compliance
We estimate that this proposed AD
affects 569 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Relocation ......................
Replacement ..................
Software installation .......
Up to 4 work-hours × $85 per hour = $340 ...........
Up to 3 work-hours × $85 per hour = $255 ...........
2 work-hours × $85 per hour = $170 .....................
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Parts cost
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$0
$1,973
0
Cost per product
Up to $340 .............
Up to $2,228 ..........
170 .........................
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Cost on U.S. operators
Up to $193,460
Up to $1,267,732
96,730
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Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules
ESTIMATED COSTS—Continued
Action
Placard Removal (2 airplanes).
Labor cost
1 work-hour × $85 per hour = $85 .........................
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
According to the manufacturer, some
of the costs of this proposed 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.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
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 determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the 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,
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Cost per product
0
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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2016–7270; Directorate Identifier 2015–
NM–116–AD.
(a) Comments Due Date
We must receive comments by August 12,
2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 737–700 and –700C series airplanes
identified in paragraphs (c)(1), (c)(2), and
(c)(3) of this AD, certificated in any category.
(1) Airplanes having supplemental type
certificate ST00830SE installed (Aviation
Partners Boeing blended winglets), as
identified in Aviation Partners Boeing
Service Bulletin AP737–27–002, Revision 2,
dated March 1, 2016.
(2) Airplanes identified in Boeing Alert
Service Bulletin 737–27A1306, dated
September 10, 2015.
(3) Airplanes identified in Aviation
Partners Service Bulletin AP737–34–005,
dated July 17, 2015.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Unsafe Condition
This AD was prompted by a report that for
airplanes with blended winglets, the nose-up
pitch trim limit and associated warning for
the horizontal stabilizer control system will
allow take-off with incorrect trim settings.
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85 ...........................
Cost on U.S. operators
170
We are issuing this AD to prevent take-off
with incorrect settings of the horizontal
stabilizer pitch trim system. Settings outside
of the appropriate pitch trim limits could
result in loss of controllability of the airplane
during take-off.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Replacement, Relocation, and Applicable
Related Investigative and Corrective Actions
(1) For airplanes identified in paragraph
(c)(1) of this AD: Within 72 months after the
effective date of this AD, relocate the position
warning horn switches of the horizontal
stabilizer, replace the pitch trim light plates
on the flight deck control stand, revise the
software, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Aviation Partners Boeing
Service Bulletin AP737–27–002, Revision 2,
dated March 1, 2016; except as specified in
paragraph (j) of this AD. Do all applicable
related investigative and corrective actions
before further flight.
(2) For airplanes identified in paragraph
(c)(2) of this AD: Within 72 months after the
effective date of this AD, relocate the position
warning horn switches of the horizontal
stabilizer, replace the pitch trim light plates
on the flight deck control stand, revise the
software, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–27A1306, dated September 10, 2015,
and Aviation Partners Boeing Service
Bulletin AP737–27–002, Revision 2, dated
March 1, 2016; except as specified in
paragraph (j) of this AD. Do all applicable
related investigative and corrective actions
before further flight.
(h) Software Revision and Placard Removal
For airplanes identified in paragraph (c)(3)
of this AD: Within 72 months after the
effective date of this AD, revise the software
and remove the placard, in accordance with
the Accomplishment Instructions of Aviation
Partners Service Bulletin AP737–34–005,
dated July 17, 2015.
(i) Credit for Actions Accomplished in
Accordance With Previous Service
Information
This paragraph provides credit for the
actions specified in paragraphs (g)(1) and
(g)(2) of this AD, if those actions were
performed before the effective date of this AD
using Aviation Partners Boeing Service
Bulletin AP737–27–002, dated March 31,
2015; or Aviation Partners Boeing Service
Bulletin AP737–27–002, Revision 1, dated
August 6, 2015.
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Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules
(j) Exception to the Service Information
Where Aviation Partners Boeing Service
Bulletin AP737–27–002, Revision 2, dated
March 1, 2016, specifies to contact Boeing for
appropriate action, and specifies that action
as Required for Compliance (RC): Before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (k) of this AD.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(k) 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 (l)(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,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair,
modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(4) Except as required by paragraph (j) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (k)(4)(i) and (k)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(l) Related Information
(1) For more information about this AD,
contact Fnu Winarto, Aerospace Engineer,
Systems and Equipment Branch, ANM–130S,
FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6659; fax: 425–
917–6590; email: fnu.winarto@faa.gov.
(2) For service information identified in
this AD, contact Aviation Partners Boeing,
2811 South 102nd Street, Suite 200, Seattle,
WA 98168; phone: 206–830–7699; fax: 206–
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767–3355; email: leng@aviationpartners.com;
Internet: https://
www.aviationpartnersboeing.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.
Issued in Renton, Washington, on June 14,
2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–14966 Filed 6–27–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–7267; Directorate
Identifier 2016–NM–015–AD]
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–102,
–103, and –106 airplanes, Model DHC–
8–200 series airplanes, and Model DHC–
8–300 series airplanes. This proposed
AD was prompted by several
occurrences of loss of airspeed data on
both pilot and co-pilot air speed
indicators due to the accumulation of
ice on the pitot probes. An investigation
revealed that the accumulation of ice
was due to inoperative pitot probe
heaters. This proposed AD would
require replacing the existing circuit
breakers in both the left and right side
of the pitot heater system with circuit
breakers that have higher trip points.
We are proposing this AD to prevent
circuit breakers from tripping and
cutting power supply to the pitot probe
heater, which could cause loss of
airspeed data and result in the
flightcrew not being able to control the
airspeed of the airplane.
DATES: We must receive comments on
this proposed AD by August 12, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
SUMMARY:
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• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, 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.
Examining the AD Docket
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You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
7267; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone: 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Assata Dessaline, Aerospace Engineer,
Avionics and Services Branch, ANE–
172, FAA, New York Aircraft
Certification Office (ACO), 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone: 516–228–7301; fax:
516–794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–7267; Directorate Identifier
2016–NM–015–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
E:\FR\FM\28JNP1.SGM
28JNP1
]]>Agencies
[Federal Register Volume 81, Number 124 (Tuesday, June 28, 2016)]
[Proposed Rules]
[Pages 41894-41897]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-14966]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-7270; Directorate Identifier 2015-NM-116-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 737-700 and -700C series airplanes.
This proposed AD was prompted by a report that for airplanes with
blended winglets, the nose-up pitch trim limit and associated warning
for the horizontal stabilizer control system will allow take-off with
incorrect trim settings. This proposed AD would require, depending on
airplane configuration, replacing the pitch trim light plates on the
flight deck control stand, relocating the position warning horn
switches of the horizontal stabilizer, revising the software, removing
the placard, and doing related investigative and corrective actions if
necessary. We are proposing this AD to prevent take-off with incorrect
settings of the horizontal stabilizer pitch trim system. Settings
outside of the appropriate pitch trim limits could result in loss of
controllability of the airplane during take-off.
DATES: We must receive comments on this proposed AD by August 12, 2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For Aviation Partners Boeing service information identified in this
NPRM, contact Aviation Partners Boeing, 2811 South 102nd Street, Suite
200, Seattle, WA 98168; phone: 206-830-7699; fax: 206-767-3355; email:
leng@aviationpartners.com; Internet: https://www.aviationpartnersboeing.com.
[[Page 41895]]
For The Boeing Company service information identified in this NPRM,
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. Boeing Alert Service Bulletin 737-27A1306, dated September
10, 2015, is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7270.
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-2016-
7270; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Fnu Winarto, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6659; fax: 425-917-6590; email:
fnu.winarto@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2016-7270;
Directorate Identifier 2015-NM-116-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received a report that for airplanes with blended winglets,
the nose-up pitch trim limit and associated warning for the horizontal
stabilizer control system will allow takeoff with incorrect trim
settings. The trim control system was recently analyzed for potential
nose-up mis-trim occurrences during take-off for airplanes with blended
winglets. Results of the analysis indicated that Model 737-700
airplanes with blended winglets are not compliant with the
certification rules for specific conditions. This condition, if not
corrected, could result in the loss of controllability of the airplane
during take-off.
Related Service Information Under 1 CFR Part 51
We reviewed Aviation Partners Boeing Service Bulletin AP737-27-002,
Revision 2, dated March 1, 2016, and Boeing Alert Service Bulletin 737-
27A1306, dated September 10, 2015. The service information describes
procedures for replacing the pitch trim light plates on the flight deck
control stand, relocating the position warning horn switches of the
horizontal stabilizer, revising the software, and doing related
investigative and corrective actions.
The related investigative actions include verifying that the
stabilizer ``B'' measurement is at a certain dimension, performing a
light plate function test, performing a stabilizer functional test,
loading and verifying model/engine database software, performing a
flight management computer configuration check, and verifying all
settings.
The corrective actions include adjusting the stabilizer, adjusting
the light plate, replacing the light plate, rigging and adjusting the
horizontal stabilizer trim system, and repairing the light plate
switch.
We reviewed Aviation Partners Service Bulletin AP737-34-005, dated
July 17, 2015. The service information describes procedures for
revising the software and removing the placard.
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.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the Service
Information.'' For information on the procedures and compliance times,
see Boeing Alert Service Bulletin 737-27A1306, dated September 10,
2015, at https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-7270.
Differences Between This Proposed AD and the Service Information
The service information specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD affects 569 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Relocation..................... Up to 4 work-hours x $0 Up to $340........ Up to $193,460
$85 per hour = $340.
Replacement.................... Up to 3 work-hours x $1,973 Up to $2,228...... Up to $1,267,732
$85 per hour = $255.
Software installation.......... 2 work-hours x $85 per 0 170............... 96,730
hour = $170.
[[Page 41896]]
Placard Removal (2 airplanes).. 1 work-hour x $85 per 0 85................ 170
hour = $85.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
According to the manufacturer, some of the costs of this proposed
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):
The Boeing Company: Docket No. FAA-2016-7270; Directorate Identifier
2015-NM-116-AD.
(a) Comments Due Date
We must receive comments by August 12, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 737-700 and -700C
series airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3)
of this AD, certificated in any category.
(1) Airplanes having supplemental type certificate ST00830SE
installed (Aviation Partners Boeing blended winglets), as identified
in Aviation Partners Boeing Service Bulletin AP737-27-002, Revision
2, dated March 1, 2016.
(2) Airplanes identified in Boeing Alert Service Bulletin 737-
27A1306, dated September 10, 2015.
(3) Airplanes identified in Aviation Partners Service Bulletin
AP737-34-005, dated July 17, 2015.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Unsafe Condition
This AD was prompted by a report that for airplanes with blended
winglets, the nose-up pitch trim limit and associated warning for
the horizontal stabilizer control system will allow take-off with
incorrect trim settings. We are issuing this AD to prevent take-off
with incorrect settings of the horizontal stabilizer pitch trim
system. Settings outside of the appropriate pitch trim limits could
result in loss of controllability of the airplane during take-off.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Replacement, Relocation, and Applicable Related Investigative and
Corrective Actions
(1) For airplanes identified in paragraph (c)(1) of this AD:
Within 72 months after the effective date of this AD, relocate the
position warning horn switches of the horizontal stabilizer, replace
the pitch trim light plates on the flight deck control stand, revise
the software, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Aviation Partners Boeing Service Bulletin AP737-27-
002, Revision 2, dated March 1, 2016; except as specified in
paragraph (j) of this AD. Do all applicable related investigative
and corrective actions before further flight.
(2) For airplanes identified in paragraph (c)(2) of this AD:
Within 72 months after the effective date of this AD, relocate the
position warning horn switches of the horizontal stabilizer, replace
the pitch trim light plates on the flight deck control stand, revise
the software, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-27A1306, dated
September 10, 2015, and Aviation Partners Boeing Service Bulletin
AP737-27-002, Revision 2, dated March 1, 2016; except as specified
in paragraph (j) of this AD. Do all applicable related investigative
and corrective actions before further flight.
(h) Software Revision and Placard Removal
For airplanes identified in paragraph (c)(3) of this AD: Within
72 months after the effective date of this AD, revise the software
and remove the placard, in accordance with the Accomplishment
Instructions of Aviation Partners Service Bulletin AP737-34-005,
dated July 17, 2015.
(i) Credit for Actions Accomplished in Accordance With Previous Service
Information
This paragraph provides credit for the actions specified in
paragraphs (g)(1) and (g)(2) of this AD, if those actions were
performed before the effective date of this AD using Aviation
Partners Boeing Service Bulletin AP737-27-002, dated March 31, 2015;
or Aviation Partners Boeing Service Bulletin AP737-27-002, Revision
1, dated August 6, 2015.
[[Page 41897]]
(j) Exception to the Service Information
Where Aviation Partners Boeing Service Bulletin AP737-27-002,
Revision 2, dated March 1, 2016, specifies to contact Boeing for
appropriate action, and specifies that action as Required for
Compliance (RC): Before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(k) of this AD.
(k) 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 (l)(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, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make those findings. For a repair method to
be approved, the repair, modification deviation, or alteration
deviation must meet the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (j) of this AD: For service
information that contains steps that are labeled as Required for
Compliance (RC), the provisions of paragraphs (k)(4)(i) and
(k)(4)(ii) of this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. An AMOC is required for any deviations to RC steps,
including substeps and identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(l) Related Information
(1) For more information about this AD, contact Fnu Winarto,
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA,
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6659; fax: 425-917-6590;
email: fnu.winarto@faa.gov.
(2) For service information identified in this AD, contact
Aviation Partners Boeing, 2811 South 102nd Street, Suite 200,
Seattle, WA 98168; phone: 206-830-7699; fax: 206-767-3355; email:
leng@aviationpartners.com; Internet: https://www.aviationpartnersboeing.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.
Issued in Renton, Washington, on June 14, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-14966 Filed 6-27-16; 8:45 am]
BILLING CODE 4910-13-P
