Airworthiness Directives; The Boeing Company Airplanes, 29792-29795 [2017-13773]
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Federal Register / Vol. 82, No. 125 / Friday, June 30, 2017 / Proposed Rules
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0217, dated November 2, 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–2017–0628.
(2) For more information about this AD,
contact 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.
(3) 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 22,
2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–13755 Filed 6–29–17; 8:45 am]
BILLING CODE 4910–13–P
We must receive comments on
this proposed AD by August 14, 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; 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–
0629.
DATES:
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0629; Directorate
Identifier 2016–NM–184–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 all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. This proposed AD was
prompted by reports of fatigue cracking
in the frame outboard chord and in the
radius of the auxiliary chord at a certain
area. This proposed AD would require
inspections to detect this cracking, and
corrective action if necessary. We are
proposing this AD to address the unsafe
condition on these products.
mstockstill on DSK30JT082PROD with PROPOSALS
SUMMARY:
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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–2017–
0629; 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:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: (425)
917–6450; fax: (425) 917–6590; email:
alan.pohl@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
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this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2017–0629; Directorate Identifier 2016–
NM–184–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 reports indicating
that fatigue cracking was found in the
frame outboard chord at BS 727 and in
the radius of the auxiliary chord at BS
727 and S–18A on certain airplanes.
Cracks in the outboard chord were
found on airplanes having between
20,000 and 85,000 flight cycles, and
between 27,000 and 74,000 flight hours.
Cracks in the radius of the auxiliary
chord were found on airplanes having
between 46,000 and 85,000 flight cycles,
and between 41,000 and 64,000 flight
hours. The cracks were caused by
fatigue, and, for certain airplanes, the
fretting of adjacent parts contributed to
the initiation of the fatigue damage. This
condition, if not corrected, could result
in reduced structural integrity of the
outboard chord and consequent rapid
decompression of the airplane.
Related Rulemaking
On October 16, 2012, we issued AD
2012–23–04, Amendment 39–17260 (77
FR 69747, November 21, 2012) (‘‘AD
2012–23–04’’), applicable to all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. That AD requires various
inspections for cracks in the outboard
chord of the frame at BS 727. That AD
also requires inspections for cracks in
the BS 727 frame outboard chord and
the radius of the auxiliary chord, for
certain airplanes. That AD was
prompted by several reports of fatigue
cracking in the frame outboard chord at
BS 727 and in the radius of the auxiliary
chord. The actions required by that AD
are intended to detect and correct
fatigue cracking of the outboard and
auxiliary chords, which could result in
reduced structural integrity of the
outboard chord and consequent rapid
decompression of the airplane.
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Federal Register / Vol. 82, No. 125 / Friday, June 30, 2017 / Proposed Rules
Since issuance of AD 2012–23–04, the
FAA has found discrepancies in the
requirements of that AD, as follows:
• The optional terminating action
specified in paragraph (r) of AD 2012–
23–04 allows terminating action if the
preventive modification is installed.
However, Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May
25, 2006, allows terminating action only
if both the BS 727 outboard chord is
replaced and the preventive
modification is installed. Consequently,
for airplanes having line numbers 1
through 999 inclusive on which the
preventive modification may have been
installed, the outboard chord may not
have been replaced. Additionally,
paragraph (r)(2) of AD 2012–23–04
specifies replacing only a cracked
outboard chord; however, the intent was
to require replacement of the outboard
chord whether it was cracked or not. In
light of these factors, there could be
cracking in the auxiliary chord
combined with cracking in the outboard
chord. This cracking could progress
undetected and result in the identified
unsafe condition.
• Boeing Alert Service Bulletin 737–
53A1166, Revision 2, dated May 25,
2006, contains instructions to determine
whether the modification should be
classified as interim or permanent; a
one-time inspection is specified after
the interim modification is done. The
instructions specified in the previous
service information did not contain this
stipulation during installation of the
preventive modification. Therefore, the
modification could have resulted in
edge margins in the frame outboard
chord that would have been classified as
interim had the modification been done
in accordance with Boeing Alert Service
Bulletin 737–53A1166, Revision 2,
dated May 25, 2006. Since neither
Boeing Alert Service Bulletin 737–
53A1166, Revision 2, dated May 25,
2006, nor AD 2012–23–04 contained
instructions to measure edge margins, it
is possible that an edge margin
condition exists, so the one-time followon inspection must be done.
• Paragraph (r) of AD 2012–23–04
terminates the one-time inspection
specified in Part 8 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1166,
Revision 2, dated May 25, 2006, for
airplanes that have the interim
preventive modification installed. This
inspection is referenced in paragraph (o)
of AD 2012–23–04, and should not have
been terminated. Paragraph (o) of AD
2012–23–04 was incorrectly included in
the list of paragraphs with inspections
that are terminated after accomplishing
paragraph (r) of that AD.
Therefore, since the discrepancies
described previously provide
inadvertent relief to operators, we find
it necessary to issue additional, new AD
rulemaking to provide additional
inspection requirements. We have
confirmed that the requirements of this
AD correct those discrepancies and do
not conflict with other requirements of
AD 2012–23–04.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1166, Revision 2,
dated May 25, 2006. The service
information describes procedures for
inspections for cracks of the BS 727
frame outboard chord and in the radius
29793
of the auxiliary chord, and repair or
replacement if necessary. 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 these same
type designs.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
the service information described
previously.
This AD corrects discrepancies in the
requirements for certain airplanes
identified in AD 2012–23–04. The FAA
has considered that fact in determining
whether to issue a new AD action or to
supersede AD 2012–23–04. We have
determined that a less burdensome
approach is to issue a separate AD
action applicable to the airplanes on
which the discrepancies could have
occurred. This proposed AD would not
supersede AD 2012–23–04, and
compliance with the requirements must
continue for airplanes listed in the
applicability of AD 2012–23–04. This
proposed AD is a separate AD action,
applicable only to the airplanes
identified in paragraph (c) of this AD.
Costs of Compliance
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Affected
airplanes of
U.S. registry
Action
Labor cost
Detailed and High Frequency Eddy
Current (HFEC) inspections.
One-time follow-on HFEC inspection ..
HFEC inspection ..................................
6 work-hours × $85 per hour = $510
per inspection cycle.
9 work-hours × $85 per hour = $765 ..
9 work-hours × $85 per hour = $765 ..
We estimate the following costs to do
any necessary repairs that would be
Cost per
product
5
5
150
required based on the results of the
inspections. We have no way of
$510
765
765
Cost on U.S. operators
$2,550 per inspection cycle.
$3,825.
$114,750.
determining the number of aircraft that
might need these repairs:
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ON-CONDITION COSTS
Action
Labor cost
Repair of cracking of the outboard chord frame ..........
Repair of cracking of the outboard chord ....................
514 work-hours × $85 per hour = $43,690 ..................
49 work-hours × $85 per hour = $4,165 ......................
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Parts cost
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$13,586
4,255
Cost per
product
$57,276
8,420
29794
Federal Register / Vol. 82, No. 125 / Friday, June 30, 2017 / Proposed Rules
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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.
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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.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2017–0629; Directorate Identifier 2016–
NM–184–AD.
(a) Comments Due Date
We must receive comments by August 14,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
fatigue cracking in the frame outboard chord
and in the radius of the auxiliary chord at
body station (BS) 727 and stringer (S) 18A.
We are issuing this AD to detect and correct
fatigue cracking of the outboard and auxiliary
chords, which could result in reduced
structural integrity of the outboard chord and
consequent rapid decompression of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections and Corrective
Action
For airplanes identified in paragraph (h) of
this AD: Within 4,500 flight cycles or 24
months after the effective date of this AD,
whichever occurs first, do internal detailed
and High Frequency Eddy Current (HFEC)
inspections to detect cracks in the auxiliary
chord radius, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1166, Revision 2,
dated May 25, 2006. If any crack is found
during any inspection required by this
paragraph, before further flight, repair using
a method approved in accordance with the
procedures specified in paragraph (l) of this
AD. Repeat the inspections thereafter at
intervals not to exceed 15,000 flight cycles.
Replacement of the outboard chord of the
frame at BS 727 concurrently with the
installation of the preventive modification of
the outboard chord in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1166,
Revision 2, dated May 25, 2006, terminates
the repetitive inspections required by this
paragraph.
(h) Airplanes for Actions Specified in
Paragraph (g) of This AD
The actions specified in paragraph (g) of
this AD are required for airplanes that meet
the criteria of paragraphs (h)(1), (h)(2), (h)(3),
and (h)(4) of this AD.
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(1) Model 737–100, –200, and –200C series
airplanes, line numbers 1 through 999
inclusive.
(2) Airplanes identified as Groups 1, 2, and
3 in Boeing Alert Service Bulletin 737–
53A1166, Revision 2, dated May 25, 2006.
(3) Airplanes on which a preventive
modification has been installed in
accordance with the method specified in
paragraph (h)(3)(i), (h)(3)(ii), or (h)(3)(iii) of
this AD.
(i) Part 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006.
(ii) Part II of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 1, dated May 25,
1995.
(iii) Part II of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, dated June 30, 1994.
(4) Airplanes on which the outboard chord
has not been replaced in accordance with the
method specified in paragraph (h)(4)(i),
(h)(4)(ii), or (h)(4)(iii) of this AD.
(i) Part 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006.
(ii) Part I of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 1, dated May 25,
1995.
(iii) Part I of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, dated June 30, 1994.
(i) Edge Margin Measurement, Related
Investigative Actions, and Repair
For Model 737–100, –200, and –200C
series airplanes having line numbers 1
through 999 inclusive, identified as Groups
1 through 3 in Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006, on which the preventive modification
has been installed in accordance with Boeing
Alert Service Bulletin 737–53A1166, dated
June 30, 1994; or Boeing Alert Service
Bulletin 737–53A1166, Revision 1, dated
May 25, 1995: Within 60,000 flight cycles
after accomplishing the preventive
modification, determine if the modification is
classified as interim or permanent by using
the edge margin measurement and repair
classification specified in Part 6 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1166, Revision 2,
dated May 25, 2006. In lieu of measuring on
the airplane, a review of engineering
documentation may be used to classify the
modification if the engineering
documentation was completed at the time of
the modification and has the edge margins
recorded.
(1) If the modification is classified as
permanent, no further action is required by
paragraph (i) of this AD.
(2) If the modification is classified as
interim: Within 60,000 flight cycles after
accomplishment of the interim modification
of the outboard chord of the frame at BS 727
at S–18A, but no earlier than 50,000 flight
cycles after accomplishment of the
modification, do a one-time follow-on openhole eddy current inspection to detect cracks
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Federal Register / Vol. 82, No. 125 / Friday, June 30, 2017 / Proposed Rules
in the modified chord, in accordance with
Part 8 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1166,
Revision 2, dated May 25, 2006. If any crack
is found, before further flight, repair in
accordance with Part 3 or Part 4, as
applicable, of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006; except, if the repairs cannot be
installed using the identified procedures,
repair before further flight using a method
approved in accordance with the procedures
specified in paragraph (l) of this AD.
(j) Follow-On Inspection for Interim
Modification and Repair
For airplanes having line numbers 1
through 3132 inclusive, on which an interim
modification of the BS 727 outboard chord as
defined in Part 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006, has been accomplished: Within 60,000
flight cycles after accomplishment of the
interim modification of the outboard chord of
the frame at BS 727 at S–18A, but no earlier
than 50,000 flight cycles after
accomplishment of the modification, do a
one-time follow-on open-hole eddy current
inspection to detect cracks in the modified
chord, in accordance with Part 8 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1166, Revision 2,
dated May 25, 2006. If any crack is found
during the inspection required by this
paragraph, before further flight, repair in
accordance with Part 3 or Part 4, as
applicable, of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006; except, where the repairs cannot be
installed using the procedures identified in
this service bulletin, repair before further
flight using a method approved in
accordance with the procedures specified in
paragraph (l) of this AD.
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(k) Exception to the Service Information
Access and restoration procedures
specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006, are not required by this AD. Operators
may do those actions following their
approved maintenance procedures.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-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.
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(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. 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.
(m) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; phone: (425) 917–6450; fax: (425) 917–
6590; email: alan.pohl@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;
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 June 22,
2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–13773 Filed 6–29–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0627; Directorate
Identifier 2017–NM–037–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A330–200 Freighter,
–200, and –300 series airplanes; and
Airbus Model A340–200, –300, –500,
and –600 series airplanes. This
proposed AD was prompted by a report
that the trimmable horizontal stabilizer
actuator (THSA) might not function as
intended after failure of the primary
load path. This proposed AD would
require repetitive detailed visual
inspections for discrepancies of the
SUMMARY:
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29795
THSA upper attachments and no-back
housing. We are proposing this AD to
address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by August 14, 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 Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@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.
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–
0627; 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
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
E:\FR\FM\30JNP1.SGM
30JNP1
]]>Agencies
[Federal Register Volume 82, Number 125 (Friday, June 30, 2017)]
[Proposed Rules]
[Pages 29792-29795]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-13773]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0629; Directorate Identifier 2016-NM-184-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 all
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. This proposed AD was prompted by reports of fatigue
cracking in the frame outboard chord and in the radius of the auxiliary
chord at a certain area. This proposed AD would require inspections to
detect this cracking, and corrective action if necessary. We are
proposing this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by August 14, 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; 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-2017-0629.
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-
0629; 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: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-
6450; fax: (425) 917-6590; email: alan.pohl@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-2017-0629;
Directorate Identifier 2016-NM-184-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 reports indicating that fatigue cracking was found
in the frame outboard chord at BS 727 and in the radius of the
auxiliary chord at BS 727 and S-18A on certain airplanes. Cracks in the
outboard chord were found on airplanes having between 20,000 and 85,000
flight cycles, and between 27,000 and 74,000 flight hours. Cracks in
the radius of the auxiliary chord were found on airplanes having
between 46,000 and 85,000 flight cycles, and between 41,000 and 64,000
flight hours. The cracks were caused by fatigue, and, for certain
airplanes, the fretting of adjacent parts contributed to the initiation
of the fatigue damage. This condition, if not corrected, could result
in reduced structural integrity of the outboard chord and consequent
rapid decompression of the airplane.
Related Rulemaking
On October 16, 2012, we issued AD 2012-23-04, Amendment 39-17260
(77 FR 69747, November 21, 2012) (``AD 2012-23-04''), applicable to all
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. That AD requires various inspections for cracks in
the outboard chord of the frame at BS 727. That AD also requires
inspections for cracks in the BS 727 frame outboard chord and the
radius of the auxiliary chord, for certain airplanes. That AD was
prompted by several reports of fatigue cracking in the frame outboard
chord at BS 727 and in the radius of the auxiliary chord. The actions
required by that AD are intended to detect and correct fatigue cracking
of the outboard and auxiliary chords, which could result in reduced
structural integrity of the outboard chord and consequent rapid
decompression of the airplane.
[[Page 29793]]
Since issuance of AD 2012-23-04, the FAA has found discrepancies in
the requirements of that AD, as follows:
The optional terminating action specified in paragraph (r)
of AD 2012-23-04 allows terminating action if the preventive
modification is installed. However, Boeing Alert Service Bulletin 737-
53A1166, Revision 2, dated May 25, 2006, allows terminating action only
if both the BS 727 outboard chord is replaced and the preventive
modification is installed. Consequently, for airplanes having line
numbers 1 through 999 inclusive on which the preventive modification
may have been installed, the outboard chord may not have been replaced.
Additionally, paragraph (r)(2) of AD 2012-23-04 specifies replacing
only a cracked outboard chord; however, the intent was to require
replacement of the outboard chord whether it was cracked or not. In
light of these factors, there could be cracking in the auxiliary chord
combined with cracking in the outboard chord. This cracking could
progress undetected and result in the identified unsafe condition.
Boeing Alert Service Bulletin 737-53A1166, Revision 2,
dated May 25, 2006, contains instructions to determine whether the
modification should be classified as interim or permanent; a one-time
inspection is specified after the interim modification is done. The
instructions specified in the previous service information did not
contain this stipulation during installation of the preventive
modification. Therefore, the modification could have resulted in edge
margins in the frame outboard chord that would have been classified as
interim had the modification been done in accordance with Boeing Alert
Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. Since
neither Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated
May 25, 2006, nor AD 2012-23-04 contained instructions to measure edge
margins, it is possible that an edge margin condition exists, so the
one-time follow-on inspection must be done.
Paragraph (r) of AD 2012-23-04 terminates the one-time
inspection specified in Part 8 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25,
2006, for airplanes that have the interim preventive modification
installed. This inspection is referenced in paragraph (o) of AD 2012-
23-04, and should not have been terminated. Paragraph (o) of AD 2012-
23-04 was incorrectly included in the list of paragraphs with
inspections that are terminated after accomplishing paragraph (r) of
that AD.
Therefore, since the discrepancies described previously provide
inadvertent relief to operators, we find it necessary to issue
additional, new AD rulemaking to provide additional inspection
requirements. We have confirmed that the requirements of this AD
correct those discrepancies and do not conflict with other requirements
of AD 2012-23-04.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1166, Revision 2,
dated May 25, 2006. The service information describes procedures for
inspections for cracks of the BS 727 frame outboard chord and in the
radius of the auxiliary chord, and repair or replacement if necessary.
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 these same type
designs.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously.
This AD corrects discrepancies in the requirements for certain
airplanes identified in AD 2012-23-04. The FAA has considered that fact
in determining whether to issue a new AD action or to supersede AD
2012-23-04. We have determined that a less burdensome approach is to
issue a separate AD action applicable to the airplanes on which the
discrepancies could have occurred. This proposed AD would not supersede
AD 2012-23-04, and compliance with the requirements must continue for
airplanes listed in the applicability of AD 2012-23-04. This proposed
AD is a separate AD action, applicable only to the airplanes identified
in paragraph (c) of this AD.
Costs of Compliance
We estimate the following costs to comply with this proposed AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Affected
airplanes Cost per
Action Labor cost of U.S. product Cost on U.S. operators
registry
--------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed and High Frequency Eddy Current 6 work-hours x $85 per hour 5 $510 $2,550 per inspection cycle.
(HFEC) inspections. = $510 per inspection cycle.
One-time follow-on HFEC inspection....... 9 work-hours x $85 per hour 5 765 $3,825.
= $765.
HFEC inspection.......................... 9 work-hours x $85 per hour 150 765 $114,750.
= $765.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the inspections. We have no
way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair of cracking of the outboard chord frame 514 work-hours x $85 per hour = $13,586 $57,276
$43,690.
Repair of cracking of the outboard chord...... 49 work-hours x $85 per hour = 4,255 8,420
$4,165.
----------------------------------------------------------------------------------------------------------------
[[Page 29794]]
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-2017-0629; Directorate Identifier
2016-NM-184-AD.
(a) Comments Due Date
We must receive comments by August 14, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of fatigue cracking in the frame
outboard chord and in the radius of the auxiliary chord at body
station (BS) 727 and stringer (S) 18A. We are issuing this AD to
detect and correct fatigue cracking of the outboard and auxiliary
chords, which could result in reduced structural integrity of the
outboard chord and consequent rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Corrective Action
For airplanes identified in paragraph (h) of this AD: Within
4,500 flight cycles or 24 months after the effective date of this
AD, whichever occurs first, do internal detailed and High Frequency
Eddy Current (HFEC) inspections to detect cracks in the auxiliary
chord radius, in accordance with Part 1 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision
2, dated May 25, 2006. If any crack is found during any inspection
required by this paragraph, before further flight, repair using a
method approved in accordance with the procedures specified in
paragraph (l) of this AD. Repeat the inspections thereafter at
intervals not to exceed 15,000 flight cycles. Replacement of the
outboard chord of the frame at BS 727 concurrently with the
installation of the preventive modification of the outboard chord in
accordance with Part 6 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006,
terminates the repetitive inspections required by this paragraph.
(h) Airplanes for Actions Specified in Paragraph (g) of This AD
The actions specified in paragraph (g) of this AD are required
for airplanes that meet the criteria of paragraphs (h)(1), (h)(2),
(h)(3), and (h)(4) of this AD.
(1) Model 737-100, -200, and -200C series airplanes, line
numbers 1 through 999 inclusive.
(2) Airplanes identified as Groups 1, 2, and 3 in Boeing Alert
Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006.
(3) Airplanes on which a preventive modification has been
installed in accordance with the method specified in paragraph
(h)(3)(i), (h)(3)(ii), or (h)(3)(iii) of this AD.
(i) Part 6 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006.
(ii) Part II of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995.
(iii) Part II of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1166, dated June 30, 1994.
(4) Airplanes on which the outboard chord has not been replaced
in accordance with the method specified in paragraph (h)(4)(i),
(h)(4)(ii), or (h)(4)(iii) of this AD.
(i) Part 3 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006.
(ii) Part I of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995.
(iii) Part I of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1166, dated June 30, 1994.
(i) Edge Margin Measurement, Related Investigative Actions, and Repair
For Model 737-100, -200, and -200C series airplanes having line
numbers 1 through 999 inclusive, identified as Groups 1 through 3 in
Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25,
2006, on which the preventive modification has been installed in
accordance with Boeing Alert Service Bulletin 737-53A1166, dated
June 30, 1994; or Boeing Alert Service Bulletin 737-53A1166,
Revision 1, dated May 25, 1995: Within 60,000 flight cycles after
accomplishing the preventive modification, determine if the
modification is classified as interim or permanent by using the edge
margin measurement and repair classification specified in Part 6 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1166, Revision 2, dated May 25, 2006. In lieu of measuring on
the airplane, a review of engineering documentation may be used to
classify the modification if the engineering documentation was
completed at the time of the modification and has the edge margins
recorded.
(1) If the modification is classified as permanent, no further
action is required by paragraph (i) of this AD.
(2) If the modification is classified as interim: Within 60,000
flight cycles after accomplishment of the interim modification of
the outboard chord of the frame at BS 727 at S-18A, but no earlier
than 50,000 flight cycles after accomplishment of the modification,
do a one-time follow-on open-hole eddy current inspection to detect
cracks
[[Page 29795]]
in the modified chord, in accordance with Part 8 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1166, Revision 2, dated May 25, 2006. If any crack is found,
before further flight, repair in accordance with Part 3 or Part 4,
as applicable, of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006;
except, if the repairs cannot be installed using the identified
procedures, repair before further flight using a method approved in
accordance with the procedures specified in paragraph (l) of this
AD.
(j) Follow-On Inspection for Interim Modification and Repair
For airplanes having line numbers 1 through 3132 inclusive, on
which an interim modification of the BS 727 outboard chord as
defined in Part 6 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006, has
been accomplished: Within 60,000 flight cycles after accomplishment
of the interim modification of the outboard chord of the frame at BS
727 at S-18A, but no earlier than 50,000 flight cycles after
accomplishment of the modification, do a one-time follow-on open-
hole eddy current inspection to detect cracks in the modified chord,
in accordance with Part 8 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25,
2006. If any crack is found during the inspection required by this
paragraph, before further flight, repair in accordance with Part 3
or Part 4, as applicable, of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25,
2006; except, where the repairs cannot be installed using the
procedures identified in this service bulletin, repair before
further flight using a method approved in accordance with the
procedures specified in paragraph (l) of this AD.
(k) Exception to the Service Information
Access and restoration procedures specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1166, Revision 2, dated May 25, 2006, are not required by this
AD. Operators may do those actions following their approved
maintenance procedures.
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (m)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, 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. 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.
(m) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: (425) 917-6450; fax: (425) 917-6590; email:
alan.pohl@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;
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 June 22, 2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-13773 Filed 6-29-17; 8:45 am]
BILLING CODE 4910-13-P
