Airworthiness Directives; The Boeing Company Airplanes, 22915-22918 [2017-10033]
Download as PDF
Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules
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
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):
■
Bombardier, Inc.: Docket No. FAA–2017–
0481; Directorate Identifier 2016–NM–
196–AD.
(a) Comments Due Date
We must receive comments by July 3, 2017.
sradovich on DSK3GMQ082PROD with PROPOSALS
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc.,
Model BD–100–1A10 airplanes, certificated
in any category, serial numbers 20003
through 20635 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 24, Electrical power.
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18:29 May 18, 2017
Jkt 241001
(e) Reason
This AD was prompted by reports of low
clearance in the aft equipment bay between
auxiliary power unit (APU) generator power
cables and a hydraulic line, which can cause
damage to wire insulation. We are issuing
this AD to prevent electrical arcing from
power cables, which could cause a fire in the
aft equipment bay.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection of APU Generator Power
Cables and Hydraulic Line, Repairs, and
Modification
Within 24 months after the effective date
of this AD, do the applicable actions required
by paragraph (g)(1) or (g)(2) of this AD.
(1) For airplanes having serial numbers
20003 through 20500 inclusive: Do a general
visual inspection of the APU generator power
cables and the adjacent hydraulic line for
damage, and do all applicable repairs; and
modify the APU generator power cable
installation; in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 100–24–28, dated July 27,
2016, except as required by paragraph (h) of
this AD. Do all applicable repairs before
further flight.
(2) For airplanes having serial numbers
20501 through 20635 inclusive: Do a general
visual inspection of the APU generator power
cables and the adjacent hydraulic line for
damage, and do all applicable repairs; and
modify the APU generator power cable
installation; in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 350–24–003, dated July 27,
2016, except as required by paragraph (h) of
this AD. Do all applicable repairs before
further flight.
(h) Exception to the Service Information
Where Bombardier Service Bulletin 100–
24–28, dated July 27, 2016, and Bombardier
Service Bulletin 350–24–003, dated July 27,
2016, specify to contact the manufacturer for
repair, before further flight, repair using a
method approved by the Manager, New York
Aircraft Certification Office (ACO), ANE–170,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO).
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO,
ANE–170, 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 ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7300; fax 516–794–5531.
Before using any approved AMOC, notify
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
22915
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office.
(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, New York ACO, ANE–170,
FAA; or TCCA; or Bombardier, Inc.’s TCCA
DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2016–28, dated
September 28, 2016, 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–2017–0481.
(2) For more information about this AD,
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.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.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 May 12,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10133 Filed 5–18–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0340; Directorate
Identifier 2017–NM–002–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 757–200,
–200PF, and –300 series airplanes. This
proposed AD was prompted by reports
SUMMARY:
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19MYP1
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Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules
of cracking found at a certain fuselage
frame inner chord. This proposed AD
would require repetitive inspections for
any cracking of a certain fuselage frame
inner chord; for certain airplanes, an
identification of the material of a certain
fuselage frame inner chord; and
applicable corrective actions. We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by July 3, 2017.
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 service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0340.
sradovich on DSK3GMQ082PROD with PROPOSALS
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–2017–
0340; 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.
VerDate Sep<11>2014
18:29 May 18, 2017
Jkt 241001
FOR FURTHER INFORMATION CONTACT:
Muoi Vuong, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5205; fax: 562–627–5210;
email: Muoi.Vuong@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–
2017–0340; Directorate Identifier 2017–
NM–002–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 indicating
that an operator found a 0.406-inch-long
crack in the fuselage station (STA) 1380
frame inner chord, originating from a
fastener hole between fuselage stringers
S–25R and S–26R. The crack was found
during frame web corrosion removal on
an airplane with a 7075–T73 aluminum
alloy at the fuselage STA 1380 frame
inner chord. Boeing received five other
reports of cracking on airplanes with a
7075–T73 aluminum alloy at the
fuselage STA 1380 frame inner chord.
Boeing has determined that existing
internal zonal general visual and
detailed structural inspections of the
number 2 cargo door cutout are not
adequate to reliably detect a crack
before it grows to a critical length. This
condition, if not corrected, could result
in the door opening during flight, and
result in rapid decompression of the
airplane and the inability to sustain
loads required for continued safe flight
and landing.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 757–53A0101, dated November
8, 2016. The service information
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Sfmt 4702
describes procedures for repetitive
surface high frequency eddy current
(HFEC) inspections for any cracking of
the fuselage STA 1380 frame inner
chord; an identification of the material
(an inspection or measurement) of the
fuselage STA 1380 frame inner chord;
and applicable corrective actions. 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 this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–20++–
+++++.
The phrase ‘‘corrective actions’’ is
used in this proposed AD. Corrective
actions correct or address any condition
found. Corrective actions in an AD
could include, for example, repairs.
Differences Between This Proposed AD
and the Service Information
Boeing Alert Service Bulletin 757–
53A0101, dated November 8, 2016,
specifies to contact the manufacturer for
certain instructions, but this proposed
AD would require using repair methods,
modification deviations, and alteration
deviations 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 588 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
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Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules
22917
ESTIMATED COSTS
Action
Labor cost
Surface HFEC inspection ...
5 work-hours × $85 per
hour = $425 per inspection cycle.
Up to 2 work-hours × $85
per hour = $170.
Identify the material ............
Parts cost
Cost per product
$0
$425 per inspection cycle .......
$249,900 per inspection cycle.
0
Up to $170 ..............................
Up to $99,960.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
List of Subjects in 14 CFR Part 39
Authority for This Rulemaking
The Proposed Amendment
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
sradovich on DSK3GMQ082PROD with PROPOSALS
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.
VerDate Sep<11>2014
18:29 May 18, 2017
Jkt 241001
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–
2017–0340; Directorate Identifier 2017–
NM–002–AD.
(a) Comments Due Date
We must receive comments by July 3, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 757–200, –200PF, and –300 series
airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin
757–53A0101, dated November 8, 2016.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
cracking found at the fuselage station (STA)
1380 frame inner chord. We are issuing this
AD to detect and correct such cracks, which
could result in the door opening during
flight, and result in rapid decompression of
the airplane and the inability to sustain loads
required for continued safe flight and
landing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection for Group 1 Airplanes
For Group 1 airplanes as identified in
Boeing Alert Service Bulletin 757–53A0101,
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Cost on U.S. operators
Frm 00014
Fmt 4702
Sfmt 4702
dated November 8, 2016: At the applicable
time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 757–53A0101, dated November 8,
2016; except as specified in paragraph (i)(1)
of this AD, do a surface high frequency eddy
current (HFEC) inspection for any cracking of
the fuselage STA 1380 frame inner chord,
and do all applicable corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–53A0101, dated November 8, 2016;
except as specified in paragraph (i)(2) of this
AD. Do all applicable corrective actions
before further flight. Repeat the surface HFEC
inspection, thereafter, at the times specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 757–53A0101, dated
November 8, 2016.
(h) Inspection for Group 2 Airplanes
For Group 2 airplanes as identified in
Boeing Alert Service Bulletin 757–53A0101,
dated November 8, 2016: At the applicable
time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 757–53A0101, dated November 8,
2016; except as specified in paragraph (i)(1)
of this AD, identify the material of the
fuselage STA 1380 frame inner chord, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–53A0101, dated November 8, 2016.
(1) If the fuselage STA 1380 frame inner
chord material 2024–T42 aluminum alloy is
found during any identification required by
paragraph (h) of this AD: No further action
is required by this AD for that airplane.
(2) If the fuselage STA 1380 frame inner
chord material 7075–T73 aluminum alloy is
found during any identification required by
paragraph (h) of this AD: Before further
flight, do a surface HFEC inspection for any
cracking of the fuselage STA 1380 frame
inner chord, and do all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 757–53A0101, dated
November 8, 2016; except as specified in
paragraph (i)(2) of this AD. Do all applicable
corrective actions before further flight.
Repeat the surface HFEC inspection,
thereafter, at the times specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 757–53A0101, dated November 8,
2016.
(i) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin
757–53A0101, dated November 8, 2016,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
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MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; 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.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles 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-LAACO-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, Los Angeles
ACO, to make those findings. To be
approved, the repair method, 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 (i)(2)
of this AD: For service information that
contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(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. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. 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.
sradovich on DSK3GMQ082PROD with PROPOSALS
(2) Where Boeing Alert Service Bulletin
757–53A0101, dated November 8, 2016,
specifies to contact Boeing for appropriate
action and identifies that action as ‘‘RC’’
(Required for Compliance): Before further
flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
Issued in Renton, Washington, on May 10,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10033 Filed 5–18–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0476; 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.
[Docket No. FAA–2017–0476; Directorate
Identifier 2016–NM–110–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2014–08–
01, for all Airbus Model A318, A319,
A320, and A321 series airplanes. AD
2014–08–01 currently requires an
inspection for part numbers of the
interconnecting struts and, for affected
interconnecting struts, identification of
the part and serial numbers of the
associated target and proximity sensors
and replacement or re-identification of
the flap interconnecting strut if
necessary. Since we issued AD 2014–
08–01, we have determined that certain
airplanes must be inspected to verify the
interconnecting strut part number. This
proposed AD would add airplanes to the
applicability. We are proposing this AD
to address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by July 3, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
(k) Related Information
11.43 and 11.45, by any of the following
(1) For more information about this AD,
methods:
contact Muoi Vuong, Aerospace Engineer,
• Federal eRulemaking Portal: Go to
Airframe Branch, ANM–120L, FAA, Los
https://www.regulations.gov. Follow the
Angeles ACO, 3960 Paramount Boulevard,
instructions for submitting comments.
Lakewood, CA 90712–4137; phone: 562–627–
• Fax: 202–493–2251.
5205; fax: 562–627–5210; email:
• Mail: U.S. Department of
Muoi.Vuong@faa.gov.
Transportation, Docket Operations, M–
(2) For service information identified in
30, West Building Ground Floor, Room
this AD, contact Boeing Commercial
W12–140, 1200 New Jersey Avenue SE.,
Airplanes, Attention: Contractual & Data
Washington, DC 20590.
Services (C&DS), 2600 Westminster Blvd.,
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18:29 May 18, 2017
Jkt 241001
• 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 Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. 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.
SUMMARY:
PO 00000
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Fmt 4702
Sfmt 4702
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
425–227–1405; fax 425–227–1149.
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–2017–0476; Directorate Identifier
2016–NM–110–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://
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.
E:\FR\FM\19MYP1.SGM
19MYP1
Agencies
[Federal Register Volume 82, Number 96 (Friday, May 19, 2017)]
[Proposed Rules]
[Pages 22915-22918]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10033]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0340; Directorate Identifier 2017-NM-002-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 757-200, -200PF, and -300 series
airplanes. This proposed AD was prompted by reports
[[Page 22916]]
of cracking found at a certain fuselage frame inner chord. This
proposed AD would require repetitive inspections for any cracking of a
certain fuselage frame inner chord; for certain airplanes, an
identification of the material of a certain fuselage frame inner chord;
and applicable corrective actions. We are proposing this AD to address
the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by July 3, 2017.
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 service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may
view this referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the
availability of this material at the FAA, call 425-227-1221. It is also
available on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2017-0340.
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-2017-
0340; 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: Muoi Vuong, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5205; fax: 562-627-5210; email: Muoi.Vuong@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-2017-0340;
Directorate Identifier 2017-NM-002-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 indicating that an operator found a
0.406-inch-long crack in the fuselage station (STA) 1380 frame inner
chord, originating from a fastener hole between fuselage stringers S-
25R and S-26R. The crack was found during frame web corrosion removal
on an airplane with a 7075-T73 aluminum alloy at the fuselage STA 1380
frame inner chord. Boeing received five other reports of cracking on
airplanes with a 7075-T73 aluminum alloy at the fuselage STA 1380 frame
inner chord. Boeing has determined that existing internal zonal general
visual and detailed structural inspections of the number 2 cargo door
cutout are not adequate to reliably detect a crack before it grows to a
critical length. This condition, if not corrected, could result in the
door opening during flight, and result in rapid decompression of the
airplane and the inability to sustain loads required for continued safe
flight and landing.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016. The service information describes procedures for
repetitive surface high frequency eddy current (HFEC) inspections for
any cracking of the fuselage STA 1380 frame inner chord; an
identification of the material (an inspection or measurement) of the
fuselage STA 1380 frame inner chord; and applicable corrective actions.
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 this service information at https://www.regulations.gov by searching
for and locating Docket No. FAA-20++-+++++.
The phrase ``corrective actions'' is used in this proposed AD.
Corrective actions correct or address any condition found. Corrective
actions in an AD could include, for example, repairs.
Differences Between This Proposed AD and the Service Information
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016,
specifies to contact the manufacturer for certain instructions, but
this proposed AD would require using repair methods, modification
deviations, and alteration deviations 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 588 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
[[Page 22917]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Surface HFEC inspection............ 5 work-hours x $0 $425 per inspection cycle............ $249,900 per inspection cycle.
$85 per hour =
$425 per
inspection
cycle.
Identify the material.............. Up to 2 work- 0 Up to $170........................... Up to $99,960.
hours x $85 per
hour = $170.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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-2017-0340; Directorate Identifier
2017-NM-002-AD.
(a) Comments Due Date
We must receive comments by July 3, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 757-200, -200PF, and
-300 series airplanes, certificated in any category, as identified
in Boeing Alert Service Bulletin 757-53A0101, dated November 8,
2016.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracking found at the
fuselage station (STA) 1380 frame inner chord. We are issuing this
AD to detect and correct such cracks, which could result in the door
opening during flight, and result in rapid decompression of the
airplane and the inability to sustain loads required for continued
safe flight and landing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection for Group 1 Airplanes
For Group 1 airplanes as identified in Boeing Alert Service
Bulletin 757-53A0101, dated November 8, 2016: At the applicable time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 757-53A0101, dated November 8, 2016; except as specified in
paragraph (i)(1) of this AD, do a surface high frequency eddy
current (HFEC) inspection for any cracking of the fuselage STA 1380
frame inner chord, and do all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 757-53A0101, dated November 8, 2016; except as
specified in paragraph (i)(2) of this AD. Do all applicable
corrective actions before further flight. Repeat the surface HFEC
inspection, thereafter, at the times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016.
(h) Inspection for Group 2 Airplanes
For Group 2 airplanes as identified in Boeing Alert Service
Bulletin 757-53A0101, dated November 8, 2016: At the applicable time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 757-53A0101, dated November 8, 2016; except as specified in
paragraph (i)(1) of this AD, identify the material of the fuselage
STA 1380 frame inner chord, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016.
(1) If the fuselage STA 1380 frame inner chord material 2024-T42
aluminum alloy is found during any identification required by
paragraph (h) of this AD: No further action is required by this AD
for that airplane.
(2) If the fuselage STA 1380 frame inner chord material 7075-T73
aluminum alloy is found during any identification required by
paragraph (h) of this AD: Before further flight, do a surface HFEC
inspection for any cracking of the fuselage STA 1380 frame inner
chord, and do all applicable corrective actions, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
757-53A0101, dated November 8, 2016; except as specified in
paragraph (i)(2) of this AD. Do all applicable corrective actions
before further flight. Repeat the surface HFEC inspection,
thereafter, at the times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016.
(i) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016, specifies a compliance time ``after the original
issue date of this service bulletin,'' this AD requires compliance
within the specified compliance time after the effective date of
this AD.
[[Page 22918]]
(2) Where Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016, specifies to contact Boeing for appropriate action
and identifies that action as ``RC'' (Required for Compliance):
Before further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (j) of this
AD.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles 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-LAACO-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, Los Angeles ACO, to make those findings. To be approved,
the repair method, 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 (i)(2) of this AD: For
service information that contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(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. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. 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.
(k) Related Information
(1) For more information about this AD, contact Muoi Vuong,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5205; fax: 562-627-5210; email: Muoi.Vuong@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this 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 May 10, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10033 Filed 5-18-17; 8:45 am]
BILLING CODE 4910-13-P