Airworthiness Directives; The Boeing Company Airplanes, 25744-25746 [2017-11257]
Download as PDF
25744
Federal Register / Vol. 82, No. 106 / Monday, June 5, 2017 / Proposed Rules
autopilot functions without automatic output
comparison. Aircraft known to have the
subject AHRS units installed include but are
not limited to the following:
(1) Dornier Luftfahrt GmbH Model 228–
100, 228–101, 228–200, 228–201, 228–202,
and 228–212 airplanes;
(2) Learjet Inc. Model 31A airplanes;
(3) Pilatus Aircraft Ltd. Model PC12, PC–
12/45, and PC–12/47 airplanes;
(4) Polskie Zaklady Lotnicze Sp. z o.o.
Model PZL M28 05 airplanes;
(5) Textron Aviation Inc. (type certificate
previously held by Cessna Aircraft Company)
Model 560XL airplanes;
(6) Bell Helicopter Textron Canada Limited
Model 407 helicopters;
(7) Bell Helicopter Textron Inc. Model 412
and 412EP helicopters; and
(8) Sikorsky Aircraft Corporation Model S–
76A, S–76–B, and S–76C helicopters.
(b) Unsafe Condition
This AD defines the unsafe condition as
the AHRS unit’s analog outputs of attitude
and heading data freezing without detection
or warning. This condition could result in
misleading attitude and heading information,
anomalous autopilot behavior, and loss of
control of the aircraft.
(c) Affected ADs
This AD affects AD 2010–26–09,
Amendment 39–16548 (75 FR 81424,
December 28, 2010). Accomplishing a certain
requirement of this AD terminates the
requirements of AD 2010–26–09.
(d) Comments Due Date
We must receive comments by August 4,
2017.
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(h) Additional Information
(1) Northrop Grumman LITEF GmbH
Service Bulletin No. 145130–0017–845,
Revision D, dated April 1, 2015, which is not
incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
this AD, contact Northrop Grumman LITEF
GmbH, Customer Service—Commercial
Avionics, Loerracher Str. 18, 79115 Freiburg,
Germany; telephone +49 (761) 4901–142; fax
+49 (761) 4901–773; email ahrs.support@nglitef.de. You may review the referenced
service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101
Hillwood Pkwy, Room 6N–321, Fort Worth,
TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2015–0093, dated May 27, 2015. You
may view the EASA AD on the Internet at
https://www.regulations.gov in the AD Docket.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 3420, Attitude and Directional Data
System.
Issued in Fort Worth, Texas, on May 19,
2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2017–11132 Filed 6–2–17; 8:45 am]
BILLING CODE 4910–13–P
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
(f) Required Actions
(1) Within 25 hours time-in-service (TIS),
remove the AHRS unit from service.
(2) Removal from service of P/N 145130–
7100 terminates the requirements of AD
2010–26–09 (75 FR 81424, December 28,
2010).
(3) Do not install an AHRS unit P/N
145130–2000, 145130–2001, 145130–7000,
145130–7001, or 145130–7100 on any
aircraft.
nlaroche on DSK30NT082PROD with PROPOSALS
(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
[Docket No. FAA–2017–0526; Directorate
Identifier 2017–NM–026–AD]
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Boston Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Send your proposal to:
Nick Rediess, Aviation Safety Engineer,
Boston Aircraft Certification Office, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, Massachusetts 01803; telephone
(781) 238–7159; email nicholas.rediess@
faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
VerDate Sep<11>2014
13:57 Jun 02, 2017
Jkt 241001
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–
0526.
ADDRESSES:
Federal Aviation Administration
14 CFR Part 39
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 cracking in the
upper aft skin at the rear spar of the
wings. This proposed AD would require
repetitive inspections for cracking of the
upper aft skin of the wings, and repair
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 July 20, 2017.
SUMMARY:
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0526; 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:
Payman Soltani, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5313; fax: 562–627–5210;
email: payman.soltani@faa.gov.
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
E:\FR\FM\05JNP1.SGM
05JNP1
25745
Federal Register / Vol. 82, No. 106 / Monday, June 5, 2017 / Proposed Rules
ADDRESSES section. Include ‘‘Docket No.
FAA–2017–0526; Directorate Identifier
2017–NM–026–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 of cracking
in the upper aft skin at the rear spar of
the wings on Model 737–200, –200C,
–300, –400, and –500 series airplanes.
One operator found a crack originating
from a fastener hole common to the
upper aft skin and strap aft of the rear
spar at wing buttock line (WBL) 187.
The airplane had accumulated 49,461
flight hours and 47,718 flight cycles. A
total of 73 cases of upper aft skin cracks
were reported between 1993 and 2015;
the cracks measured from 0.02 to 3.0
inches long. Cracks between WBL 159
and WBL 200 were found during openhole high frequency eddy current
(HFEC) inspections of a previous repair
of the upper chord splice of the wing
rear spar. The majority of larger cracks
were found at WBL 171, 183, 187, and
200 at the end fasteners common to the
straps attaching the wing trailing edge to
the wing upper aft skin. This condition,
if not corrected, could result in the
inability of a principal structural
element to sustain limit load, and
consequent reduced structural integrity
of the airplane.
Explanation of Applicability
Model 737–100, –200, and –200C
series airplanes having line numbers 1
through 291 have a limit of validity
(LOV) of 34,000 total flight cycles, and
the actions proposed in this NPRM, as
specified in Boeing Alert Service
Bulletin 737–57A1329, dated January
16, 2017, would be required at a
compliance time occurring after that
LOV. Although operation of an airplane
beyond its LOV is prohibited by 14 CFR
121.1115 and 129.115, this NPRM
includes those airplanes in the
applicability so that they are tracked in
the event the LOV is extended in the
future.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–57A1329, dated January
16, 2017. The service information
describes procedures for repetitive
surface HFEC, low frequency eddy
current, and detailed inspections on
airplanes with or without an external
repair, for cracking of the upper aft skin
from WBL 159 to WBL 220. 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. 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–2017–
0526.
Costs of Compliance
We estimate that this proposed AD
affects 471 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ...............
Up to 9 work-hours × $85 per hour = up to $765 per inspection cycle.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
nlaroche on DSK30NT082PROD with PROPOSALS
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
VerDate Sep<11>2014
13:57 Jun 02, 2017
Jkt 241001
$0
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,
PO 00000
Frm 00004
Cost per
product
Parts cost
Fmt 4702
Sfmt 4702
Up to $765 per inspection cycle.
Cost on U.S.
operators
Up to $360,315 per
inspection cycle
(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:
E:\FR\FM\05JNP1.SGM
05JNP1
25746
Federal Register / Vol. 82, No. 106 / Monday, June 5, 2017 / Proposed Rules
inspection thereafter at the applicable time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–57A1329,
dated January 16, 2017.
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–
2017–0526; Directorate Identifier 2017–
NM–026–AD.
(a) Comments Due Date
We must receive comments by July 20,
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 57; Wings.
(e) Unsafe Condition
This AD was prompted by reports of
cracking in the upper aft skin at the rear spar
of the wings. We are issuing this AD to detect
and correct cracks in the upper aft skin of the
wings, which could result in the inability of
a principle structural element to sustain limit
load, and consequent reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
nlaroche on DSK30NT082PROD with PROPOSALS
(g) For Group 1 Airplanes: Inspections
For airplanes identified as Group 1 in
Boeing Alert Service Bulletin 737–57A1329,
dated January 16, 2017: Within 120 days after
the effective date of this AD, do an inspection
for cracking of the upper aft skin of the
wings, using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD.
(h) For Groups 2 and 3 Airplanes: Repetitive
Inspections and Repair
For Groups 2 and 3 airplanes identified in
Boeing Alert Service Bulletin 737–57A1329,
dated January 16, 2017: At the applicable
time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–57A1329, dated January 16,
2017, except as required by paragraph (i) of
this AD, do the applicable inspection for
cracking of the upper aft skin of the wings
from wing buttock line (WBL) 159 to WBL
220, in accordance with the Work
Instructions of Boeing Alert Service Bulletin
737–57A1329, dated January 16, 2017. If any
cracking is found, repair before further flight,
in accordance with the procedures specified
in paragraph (j) of this AD. Repeat the
VerDate Sep<11>2014
13:57 Jun 02, 2017
Jkt 241001
(i) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin
737–57A1329, dated January 16, 2017,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
paragraph (h) of this AD requires compliance
within the specified compliance time after
the effective date of this AD.
(2) Although Boeing Alert Service Bulletin
737–57A1329, dated January 16, 2017,
specifies to contact Boeing for repair
instructions, and specifies that action as
‘‘RC’’ (Required for Compliance), this AD
requires repair 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-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 Required
for Compliance (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.
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
(k) Related Information
(1) For more information about this AD,
contact Payman Soltani, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5313; fax: 562–627–5210; email:
payman.soltani@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 May 23,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–11257 Filed 6–2–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0528; Directorate
Identifier 2017–NM–028–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model CL–600–2B16
(CL–604 Variant) airplanes. This
proposed AD was prompted by reports
of in-service incidents regarding the loss
of all air data system information
provided to the flightcrew. This
proposed AD would require revising the
airplane flight manual to provide
‘‘Unreliable Airspeed’’ procedures to the
flightcrew to stabilize the airplane’s
airspeed and attitude for continued safe
flight and landing. We are proposing
this AD to address the unsafe condition
on these products.
DATES: We must receive comments on
this proposed AD by July 20, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
SUMMARY:
E:\FR\FM\05JNP1.SGM
05JNP1
Agencies
[Federal Register Volume 82, Number 106 (Monday, June 5, 2017)]
[Proposed Rules]
[Pages 25744-25746]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-11257]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0526; Directorate Identifier 2017-NM-026-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 cracking
in the upper aft skin at the rear spar of the wings. This proposed AD
would require repetitive inspections for cracking of the upper aft skin
of the wings, and repair 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 July 20, 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-2017-0526.
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-
0526; 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: Payman Soltani, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5313; fax: 562-627-5210; email: payman.soltani@faa.gov.
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
[[Page 25745]]
ADDRESSES section. Include ``Docket No. FAA-2017-0526; Directorate
Identifier 2017-NM-026-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 of cracking in the upper aft skin at the
rear spar of the wings on Model 737-200, -200C, -300, -400, and -500
series airplanes. One operator found a crack originating from a
fastener hole common to the upper aft skin and strap aft of the rear
spar at wing buttock line (WBL) 187. The airplane had accumulated
49,461 flight hours and 47,718 flight cycles. A total of 73 cases of
upper aft skin cracks were reported between 1993 and 2015; the cracks
measured from 0.02 to 3.0 inches long. Cracks between WBL 159 and WBL
200 were found during open-hole high frequency eddy current (HFEC)
inspections of a previous repair of the upper chord splice of the wing
rear spar. The majority of larger cracks were found at WBL 171, 183,
187, and 200 at the end fasteners common to the straps attaching the
wing trailing edge to the wing upper aft skin. This condition, if not
corrected, could result in the inability of a principal structural
element to sustain limit load, and consequent reduced structural
integrity of the airplane.
Explanation of Applicability
Model 737-100, -200, and -200C series airplanes having line numbers
1 through 291 have a limit of validity (LOV) of 34,000 total flight
cycles, and the actions proposed in this NPRM, as specified in Boeing
Alert Service Bulletin 737-57A1329, dated January 16, 2017, would be
required at a compliance time occurring after that LOV. Although
operation of an airplane beyond its LOV is prohibited by 14 CFR
121.1115 and 129.115, this NPRM includes those airplanes in the
applicability so that they are tracked in the event the LOV is extended
in the future.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-57A1329, dated
January 16, 2017. The service information describes procedures for
repetitive surface HFEC, low frequency eddy current, and detailed
inspections on airplanes with or without an external repair, for
cracking of the upper aft skin from WBL 159 to WBL 220. 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. 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-2017-
0526.
Costs of Compliance
We estimate that this proposed AD affects 471 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection....................... Up to 9 work-hours $0 Up to $765 per Up to $360,315 per
x $85 per hour = inspection cycle. inspection cycle
up to $765 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
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:
[[Page 25746]]
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-2017-0526; Directorate Identifier
2017-NM-026-AD.
(a) Comments Due Date
We must receive comments by July 20, 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 57; Wings.
(e) Unsafe Condition
This AD was prompted by reports of cracking in the upper aft
skin at the rear spar of the wings. We are issuing this AD to detect
and correct cracks in the upper aft skin of the wings, which could
result in the inability of a principle structural element to sustain
limit load, and consequent reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) For Group 1 Airplanes: Inspections
For airplanes identified as Group 1 in Boeing Alert Service
Bulletin 737-57A1329, dated January 16, 2017: Within 120 days after
the effective date of this AD, do an inspection for cracking of the
upper aft skin of the wings, using a method approved in accordance
with the procedures specified in paragraph (j) of this AD.
(h) For Groups 2 and 3 Airplanes: Repetitive Inspections and Repair
For Groups 2 and 3 airplanes identified in Boeing Alert Service
Bulletin 737-57A1329, dated January 16, 2017: At the applicable time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-57A1329, dated January 16, 2017, except as required by
paragraph (i) of this AD, do the applicable inspection for cracking
of the upper aft skin of the wings from wing buttock line (WBL) 159
to WBL 220, in accordance with the Work Instructions of Boeing Alert
Service Bulletin 737-57A1329, dated January 16, 2017. If any
cracking is found, repair before further flight, in accordance with
the procedures specified in paragraph (j) of this AD. Repeat the
inspection thereafter at the applicable time specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1329,
dated January 16, 2017.
(i) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin 737-57A1329, dated
January 16, 2017, specifies a compliance time ``after the original
issue date of this service bulletin,'' paragraph (h) of this AD
requires compliance within the specified compliance time after the
effective date of this AD.
(2) Although Boeing Alert Service Bulletin 737-57A1329, dated
January 16, 2017, specifies to contact Boeing for repair
instructions, and specifies that action as ``RC'' (Required for
Compliance), this AD requires repair 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 Required
for Compliance (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 Payman Soltani,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5313; fax: 562-627-5210; email: payman.soltani@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 May 23, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-11257 Filed 6-2-17; 8:45 am]
BILLING CODE 4910-13-P