Airworthiness Directives; The Boeing Company Airplanes, 15284-15287 [2017-05768]
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Federal Register / Vol. 82, No. 58 / Tuesday, March 28, 2017 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9068; Directorate
Identifier 2016–NM–067–AD; Amendment
39–18838; AD 2017–06–14]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–300,
–400, and –500 series airplanes. This
AD was prompted by reports of cracks
in the horizontal stabilizer lower skins.
This AD requires inspections for
cracking of the horizontal stabilizer
lower skin, and corrective actions if
necessary; and also provides actions
that would terminate certain repetitive
inspections. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective May 2, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 2, 2017.
ADDRESSES: For service information
identified in this final rule, 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–2016–
9068.
DATES:
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9068; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
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16:44 Mar 27, 2017
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Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
George Garrido, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5232; fax: 562–627–5210;
email: george.garrido@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 737–300, –400, and –500 series
airplanes. The NPRM published in the
Federal Register on September 8, 2016
(81 FR 62022) (‘‘the NPRM’’). The
NPRM was prompted by reports of
cracks in the horizontal stabilizer lower
skins. The NPRM proposed to require
inspections for cracking of the
horizontal stabilizer lower skin,
including repetitive inspections, as
applicable, and corrective actions if
necessary; and also proposed actions
that would terminate certain repetitive
inspections. We are issuing this AD to
detect and correct cracks in horizontal
stabilizer lower skins resulting in
reduced local stiffness of the horizontal
stabilizer, which can cause heavy
vibration leading to loss of structural
integrity of the horizontal stabilizer.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Support for the NPRM
Boeing expressed support for the
NPRM.
Request To Revise Repair Instructions
All Nippon Airways (ANA) requested
that we revise paragraphs (h)(1) and
(h)(3) of the proposed AD to state
‘‘repair common to the rear spar lower
chord between station (STA) 83.50 and
STA 249.10,’’ instead of ‘‘repair.’’ ANA
stated that there might be a repair
installed on the lower skin of the
horizontal stabilizer that is not
addressed in Boeing Special Attention
Service Bulletin 737–55–1059, Revision
1, dated April 6, 2016 (‘‘SASB 737–55–
1059 R1’’). ANA explained that some
structural repair manual repairs and
external doublers are not applicable to
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the inspection area specified in SASB
737–55–1059 R1.
We agree with ANA’s request.
Specifying the location of the applicable
repairs may reduce potential confusion.
Therefore, we have revised paragraphs
(h)(1), (h)(2), and (h)(3) of this AD to
specify the location of the applicable
repairs.
Request To Clarify Fastener
Requirements
ANA requested that we clarify the
fastener requirements. ANA stated that
figure 3 in Boeing Special Attention
Service Bulletin 737–55–1059, dated
September 10, 1998, specifies to use
blind rivets and Hi-lok fasteners;
however, compliance table 2, note (b),
in SASB 737–55–1059 R1, states that
doublers installed with solid rivets do
not need to be inspected for any loose
or missing fasteners. ANA explained
that Boeing told ANA that Hi-lok
fasteners do not require inspection for
any loose or missing fasteners.
We agree to clarify the fastener
requirements. We infer that ANA is
requesting that we update paragraph (h)
of this AD to specify that Hi-lok
fasteners do not require inspection. We
have determined that Hi-lok fasteners
do not require inspection. Therefore, we
have added paragraph (i)(3) to this AD
to specify that where SASB 737–55–
1059 R1 specifies that doublers installed
with solid rivets do not need to be
inspected for loose or missing fasteners,
this AD does not require doublers
installed with solid rivets or Hi-lok
fasteners to be inspected for loose or
missing fasteners. We have also revised
paragraph (h)(1) of this AD to reference
this exception.
Request To Revise Configuration
Description
ANA requested that we revise
paragraph (h) of the proposed AD to
refer to the horizontal stabilizer
configuration with the applicable repair
installed side only. ANA asserted that
the wording of paragraph (h) of the
proposed AD could be interpreted to
require inspection of both the repaired
and unrepaired sides of the horizontal
stabilizer.
We agree with ANA’s request. The
wording in the proposed AD is not clear
regarding what is required if an airplane
has left and right stabilizers that are
different configurations. For example,
the left-side stabilizer may have a repair
installed common to the rear spar lower
chord (configuration 2), whereas the
right side may not have a repair
(configuration 1). We have revised the
affected airplanes in paragraph (g) of
this AD from ‘‘Group 1, Configuration 1,
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Federal Register / Vol. 82, No. 58 / Tuesday, March 28, 2017 / Rules and Regulations
final rule. Therefore, for airplanes on
which STC ST01219SE is installed, a
‘‘change in product’’ AMOC approval
request is not necessary to comply with
the requirements of 14 CFR 39.17.
airplanes’’ to ‘‘any Configuration 1
horizontal stabilizer on Group 1
airplanes’’. We have revised the affected
products in paragraph (h) of this AD
from ‘‘Group 1, Configuration 2,
airplanes’’ to ‘‘any Configuration 2
horizontal stabilizer on Group 1
airplanes.’’
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing the Supplemental Type
Certificate (STC) ST01219SE does not
affect the actions specified in the
NPRM.
We concur with the commenter. We
have redesignated paragraph (c) of the
proposed AD as paragraph (c)(1) of this
AD and added paragraph (c)(2) to this
AD to state that installation of STC
ST01219SE does not affect the ability to
accomplish the actions required by this
15285
Related Service Information Under 1
CFR Part 51
We reviewed SASB 737–55–1059 R1.
The service information describes
procedures for doing inspections of the
horizontal stabilizer lower skin, and
repairs. The service information also
describes procedures for doing actions
that would terminate certain repetitive
inspections. 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.
Costs of Compliance
We estimate that this AD affects 270
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Inspection ..........
4 work-hours × $85 per hour = $340 per inspection cycle.
$0
Cost per product
Cost on U.S. operators
$340 per inspection cycle ......
$91,800 per inspection cycle.
ESTIMATED COSTS FOR OPTIONAL ACTIONS
Action
Labor cost
Modification .................................
Up to 51 work-hours per stabilizer × $85 per hour = $4,335 ..
We estimate the following costs to do
any necessary repairs that will be
Parts cost
required based on the results of the
inspection. We have no way of
$721
Cost per product
Up to $5,056 per stabilizer.
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Labor cost
Skin splice repair ........................
External doubler repair ...............
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Action
Up to 438 work-hours × $85 per hour = $37,230 ....................
26 work-hours × $85 per hour = $2,210 ..................................
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
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16:44 Mar 27, 2017
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Parts cost
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
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$0
0
Cost per product
Up to $37,230.
$2,210.
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Federal Register / Vol. 82, No. 58 / Tuesday, March 28, 2017 / Rules and Regulations
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–06–14 The Boeing Company:
Amendment 39–18838; Docket No.
FAA–2016–9068; Directorate Identifier
2016–NM–067–AD.
(a) Effective Date
This AD is effective May 2, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–300, –400, and –500
series airplanes, certificated in any category,
as identified in Boeing Special Attention
Service Bulletin 737–55–1059, Revision 1,
dated April 6, 2016 (‘‘SASB 737–55–1059
R1’’).
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$FILE/
ST01219SE.pdf) does not affect the ability to
accomplish the actions required by this AD.
Therefore, for airplanes on which STC
ST01219SE is installed, a ‘‘change in
product’’ alternative method of compliance
(AMOC) approval request is not necessary to
comply with the requirements of 14 CFR
39.17.
(d) Subject
Air Transport Association (ATA) of
America Code 55; Horizontal stabilizer.
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(e) Unsafe Condition
This AD was prompted by reports of cracks
in horizontal stabilizer lower skins. We are
issuing this AD to detect and correct cracks
in horizontal stabilizer lower skins, resulting
in reduced local stiffness of the stabilizer,
which can cause heavy vibration leading to
loss of structural integrity of the horizontal
stabilizer.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspections, Related Investigative
Actions, and Corrective Actions for
Configuration 1 Horizontal Stabilizers on
Group 1 Airplanes
For any Configuration 1 horizontal
stabilizer on Group 1 airplanes, as identified
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16:44 Mar 27, 2017
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in SASB 737–55–1059 R1: Except as
specified in paragraph (i)(1) of this AD, at the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of SASB 737–55–1059 R1, do
a detailed inspection for cracking of the
horizontal stabilizer lower skin; and do all
applicable related investigative and
corrective actions; in accordance with the
Accomplishment Instructions of SASB 737–
55–1059 R1, except as specified in paragraph
(i)(2) of this AD. Do all applicable related
investigative and corrective actions before
further flight. Repeat the inspection of the
horizontal stabilizer lower skin, if applicable,
thereafter at the applicable intervals specified
in paragraph 1.E., ‘‘Compliance,’’ of SASB
737–55–1059 R1. Options specified in SASB
737–55–1059 R1 for accomplishing the
inspections are acceptable for the
corresponding requirements of this paragraph
provided that the inspections are done at the
applicable times in paragraph 1.E.,
‘‘Compliance,’’ of the SASB 737–55–1059 R1.
(h) Inspections, Related Investigative
Actions, and Corrective Actions for
Configuration 2 Horizontal Stabilizers on
Group 1 Airplanes
For any Configuration 2 horizontal
stabilizer on Group 1 airplanes, as identified
in SASB 737–55–1059 R1: Except as
specified in paragraph (i)(1) of this AD, at the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of SASB 737–55–1059 R1, do
the actions specified in paragraphs (h)(1),
(h)(2), and (h)(3) of this AD; and do all
applicable related investigative and
corrective actions; in accordance with the
Accomplishment Instructions of SASB 737–
55–1059 R1, except as specified in paragraph
(i)(2) of this AD. Do all applicable related
investigative and corrective actions before
further flight. Repeat the inspections
specified in paragraphs (h)(1), (h)(2), and
(h)(3) of this AD, if applicable, thereafter at
the applicable intervals specified in
paragraph 1.E., ‘‘Compliance,’’ of SASB 737–
55–1059 R1. Options specified in SASB 737–
55–1059 R1, for accomplishing the
inspections are acceptable for the
corresponding requirements of this paragraph
provided that the inspections are done at the
applicable times in paragraph 1.E.,
‘‘Compliance,’’ of SASB 737–55–1059 R1.
(1) Do a high frequency eddy current
inspection for cracking of the skin around
any repair common to the rear spar lower
chord between station (STA) 83.50 and STA
249.10 which was done as specified in the
structural repair manual or any external
doubler repair, and a detailed inspection for
any loose or any missing fastener of repaired
doublers, except as specified in paragraph
(i)(3) of this AD.
(2) Do a detailed inspection for cracking of
the inspar lower skin between STA 83.50 and
STA 249.10, except in areas repaired
common to the rear spar lower chord.
(3) Do a low frequency eddy current
inspection for cracking of the forward
fastener row of any external doubler repair
common to the rear spar lower chord
between STA 83.50 and STA 249.10.
(i) Service Information Exceptions
(1) Where SASB 737–55–1059 R1 specifies
a compliance time ‘‘after the Revision 1 date
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of this service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(2) If any cracking, corrosion, hole
elongation, or loose or missing fastener is
found during any inspection required by this
AD, and SASB 737–55–1059 R1 specifies to
contact Boeing for repair instructions: Before
further flight, repair the cracking, corrosion,
hole elongation, loose or missing fasteners
using a method approved in accordance with
the procedures specified in paragraph (j) of
this AD.
(3) Where SASB 737–55–1059 R1 specifies
that doublers installed with solid rivets do
not need to be inspected for loose or missing
fasteners, this AD does not require doublers
installed with solid rivets or Hi-lok fasteners
to be inspected for loose or missing fasteners.
(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) 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.
(k) Related Information
For more information about this AD,
contact George Garrido, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5232; fax: 562–627–5210; email:
george.garrido@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Special Attention Service
Bulletin 737–55–1059, Revision 1, dated
April 6, 2016.
(ii) Reserved.
(3) For Boeing service information
identified in this AD, contact Boeing
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Federal Register / Vol. 82, No. 58 / Tuesday, March 28, 2017 / Rules and Regulations
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.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March
16, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–05768 Filed 3–27–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–3705; Directorate
Identifier 2015–NM–168–AD; Amendment
39–18837; AD 2017–06–13]
RIN 2120–AA64
Airworthiness Directives; Textron
Aviation Inc. (Type Certificate
Previously Held by Cessna Aircraft
Company) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Textron Aviation Inc. (Textron) Model
680 airplanes. This AD was prompted
by Textron’s report of a manufacturing
defect that affects the durability of the
aft canted bulkhead metallic structure.
This AD requires repetitive inspections
of the aft canted bulkhead; repair if
necessary; and a modification, which
would terminate the repetitive
inspections. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective May 2, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 2, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Textron Aviation Inc., P.O. Box 7706,
Wichita, KS 67277; telephone 316–517–
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16:44 Mar 27, 2017
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
3705; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Phuoc Le, Aerospace Engineer, Airframe
Branch, ACE–118W, Wichita Aircraft
Certification Office (ACO), FAA, 1801
Airport Road, Room 100, Dwight D.
Eisenhower Airport, Wichita, KS 67209;
phone: 316–946–4195; fax: 316–946–
4107; email: phuoc.le@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
SUMMARY:
VerDate Sep<11>2014
6215; fax 316–517–5802; email
citationpubs@txtav.com; Internet
https://support.cessna.com/custsupt/
csupport/newlogin.jsp. You may review
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–2016–
3705.
Jkt 241001
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Textron Aviation Inc.
Model 680 airplanes. The NPRM
published in the Federal Register on
February 26, 2016 (81 FR 9790) (‘‘the
NPRM’’). The NPRM was prompted by
Textron’s report of a manufacturing
defect that affects the durability of the
aft canted bulkhead metallic structure.
The manufacturing defect directly
affects the bond integrity of the vertical
and horizontal stiffeners on the aft
canted bulkhead metallic structure. The
NPRM proposed to require repetitive
inspections of the aft canted bulkhead
and repair if necessary. The NPRM also
proposed to require a modification
which would terminate the repetitive
inspections. We are issuing this AD to
prevent disbonding of the horizontal
and vertical stiffeners on the aft canted
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15287
bulkhead. Loss of bond integrity could
result in a structural failure that could
lead to separation of the cruciform tail
and loss of control of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Limit Findings to
‘‘Disbonding’’
NetJets Aviation, Inc. (NetJets)
requested that we revise paragraph (h)
of the proposed AD to remove ‘‘cracked
paint’’ as a possible finding from the
inspection. NetJets acknowledged that
cracked paint, while not a safety
concern on its own, should be
investigated to ensure that it is not
evidence of disbonding. NetJets
indicated that the requirement for a
disbond to be repaired per an alternative
method of compliance (AMOC) is
sufficient to ensure that the safety
concern is addressed appropriately.
We agree with the commenter that
cracked paint may not be a safety
concern on its own; however it is
evidence that a disbond of the structure
may have occurred and should be
investigated further to ensure there is no
evidence of disbonding. Thus, if cracked
paint is found, operators must contact
the FAA for procedures to determine
whether the cracked paint was an
indication of disbonding. We have
revised paragraph (h) of this AD to
clarify that operators must obtain
instructions from the FAA and comply
with those instructions.
Request To Have Cessna Engineering
Drawing Be Made Available
NetJets indicated that paragraph (n)(2)
of the proposed AD states that the
required service information is available
from Textron. However, Netjets stated
that Textron does not provide owners/
operators with access to Cessna
Engineering Drawing 6991115
(‘‘Drawing 6991115’’), which is required
for compliance with paragraph (i) of the
proposed AD. NetJets added that the
required service information is not
available at the Federal Register and is
not available to owners/operators
through the source identified in the
proposed AD. NetJets indicated that
Cessna Service Bulletin SB680–53–08,
dated September 28, 2015, states that
only Textron-owned service centers can
complete the modification and have
access to Drawing 6991115. NetJets
stated that access to Drawing 6991115
should be made available to owners/
operators, and the proposed AD should
E:\FR\FM\28MRR1.SGM
28MRR1
Agencies
[Federal Register Volume 82, Number 58 (Tuesday, March 28, 2017)]
[Rules and Regulations]
[Pages 15284-15287]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-05768]
[[Page 15284]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9068; Directorate Identifier 2016-NM-067-AD;
Amendment 39-18838; AD 2017-06-14]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 737-300, -400, and -500 series airplanes. This
AD was prompted by reports of cracks in the horizontal stabilizer lower
skins. This AD requires inspections for cracking of the horizontal
stabilizer lower skin, and corrective actions if necessary; and also
provides actions that would terminate certain repetitive inspections.
We are issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective May 2, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 2, 2017.
ADDRESSES: For service information identified in this final rule,
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-2016-
9068.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9068; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: George Garrido, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5232; fax: 562-627-5210; email: george.garrido@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain The Boeing Company
Model 737-300, -400, and -500 series airplanes. The NPRM published in
the Federal Register on September 8, 2016 (81 FR 62022) (``the NPRM'').
The NPRM was prompted by reports of cracks in the horizontal stabilizer
lower skins. The NPRM proposed to require inspections for cracking of
the horizontal stabilizer lower skin, including repetitive inspections,
as applicable, and corrective actions if necessary; and also proposed
actions that would terminate certain repetitive inspections. We are
issuing this AD to detect and correct cracks in horizontal stabilizer
lower skins resulting in reduced local stiffness of the horizontal
stabilizer, which can cause heavy vibration leading to loss of
structural integrity of the horizontal stabilizer.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Support for the NPRM
Boeing expressed support for the NPRM.
Request To Revise Repair Instructions
All Nippon Airways (ANA) requested that we revise paragraphs (h)(1)
and (h)(3) of the proposed AD to state ``repair common to the rear spar
lower chord between station (STA) 83.50 and STA 249.10,'' instead of
``repair.'' ANA stated that there might be a repair installed on the
lower skin of the horizontal stabilizer that is not addressed in Boeing
Special Attention Service Bulletin 737-55-1059, Revision 1, dated April
6, 2016 (``SASB 737-55-1059 R1''). ANA explained that some structural
repair manual repairs and external doublers are not applicable to the
inspection area specified in SASB 737-55-1059 R1.
We agree with ANA's request. Specifying the location of the
applicable repairs may reduce potential confusion. Therefore, we have
revised paragraphs (h)(1), (h)(2), and (h)(3) of this AD to specify the
location of the applicable repairs.
Request To Clarify Fastener Requirements
ANA requested that we clarify the fastener requirements. ANA stated
that figure 3 in Boeing Special Attention Service Bulletin 737-55-1059,
dated September 10, 1998, specifies to use blind rivets and Hi-lok
fasteners; however, compliance table 2, note (b), in SASB 737-55-1059
R1, states that doublers installed with solid rivets do not need to be
inspected for any loose or missing fasteners. ANA explained that Boeing
told ANA that Hi-lok fasteners do not require inspection for any loose
or missing fasteners.
We agree to clarify the fastener requirements. We infer that ANA is
requesting that we update paragraph (h) of this AD to specify that Hi-
lok fasteners do not require inspection. We have determined that Hi-lok
fasteners do not require inspection. Therefore, we have added paragraph
(i)(3) to this AD to specify that where SASB 737-55-1059 R1 specifies
that doublers installed with solid rivets do not need to be inspected
for loose or missing fasteners, this AD does not require doublers
installed with solid rivets or Hi-lok fasteners to be inspected for
loose or missing fasteners. We have also revised paragraph (h)(1) of
this AD to reference this exception.
Request To Revise Configuration Description
ANA requested that we revise paragraph (h) of the proposed AD to
refer to the horizontal stabilizer configuration with the applicable
repair installed side only. ANA asserted that the wording of paragraph
(h) of the proposed AD could be interpreted to require inspection of
both the repaired and unrepaired sides of the horizontal stabilizer.
We agree with ANA's request. The wording in the proposed AD is not
clear regarding what is required if an airplane has left and right
stabilizers that are different configurations. For example, the left-
side stabilizer may have a repair installed common to the rear spar
lower chord (configuration 2), whereas the right side may not have a
repair (configuration 1). We have revised the affected airplanes in
paragraph (g) of this AD from ``Group 1, Configuration 1,
[[Page 15285]]
airplanes'' to ``any Configuration 1 horizontal stabilizer on Group 1
airplanes''. We have revised the affected products in paragraph (h) of
this AD from ``Group 1, Configuration 2, airplanes'' to ``any
Configuration 2 horizontal stabilizer on Group 1 airplanes.''
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing the Supplemental
Type Certificate (STC) ST01219SE does not affect the actions specified
in the NPRM.
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as paragraph (c)(1) of this AD and added paragraph
(c)(2) to this AD to state that installation of STC ST01219SE does not
affect the ability to accomplish the actions required by this final
rule. Therefore, for airplanes on which STC ST01219SE is installed, a
``change in product'' AMOC approval request is not necessary to comply
with the requirements of 14 CFR 39.17.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed SASB 737-55-1059 R1. The service information describes
procedures for doing inspections of the horizontal stabilizer lower
skin, and repairs. The service information also describes procedures
for doing actions that would terminate certain repetitive inspections.
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.
Costs of Compliance
We estimate that this AD affects 270 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection........................ 4 work-hours x $85 $0 $340 per inspection $91,800 per
per hour = $340 per cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
Parts
Action Labor cost cost Cost per product
----------------------------------------------------------------------------------------------------------------
Modification............................. Up to 51 work-hours per $721 Up to $5,056 per stabilizer.
stabilizer x $85 per hour =
$4,335.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
will be required based on the results of the inspection. We have no way
of determining the number of aircraft that might need these repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Parts
Action Labor cost cost Cost per product
----------------------------------------------------------------------------------------------------------------
Skin splice repair....................... Up to 438 work-hours x $85 $0 Up to $37,230.
per hour = $37,230.
External doubler repair.................. 26 work-hours x $85 per hour 0 $2,210.
= $2,210.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 15286]]
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2017-06-14 The Boeing Company: Amendment 39-18838; Docket No. FAA-
2016-9068; Directorate Identifier 2016-NM-067-AD.
(a) Effective Date
This AD is effective May 2, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-300, -400,
and -500 series airplanes, certificated in any category, as
identified in Boeing Special Attention Service Bulletin 737-55-1059,
Revision 1, dated April 6, 2016 (``SASB 737-55-1059 R1'').
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 55; Horizontal
stabilizer.
(e) Unsafe Condition
This AD was prompted by reports of cracks in horizontal
stabilizer lower skins. We are issuing this AD to detect and correct
cracks in horizontal stabilizer lower skins, resulting in reduced
local stiffness of the stabilizer, which can cause heavy vibration
leading to loss of structural integrity of the horizontal
stabilizer.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections, Related Investigative Actions, and Corrective Actions
for Configuration 1 Horizontal Stabilizers on Group 1 Airplanes
For any Configuration 1 horizontal stabilizer on Group 1
airplanes, as identified in SASB 737-55-1059 R1: Except as specified
in paragraph (i)(1) of this AD, at the applicable time specified in
paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1, do a
detailed inspection for cracking of the horizontal stabilizer lower
skin; and do all applicable related investigative and corrective
actions; in accordance with the Accomplishment Instructions of SASB
737-55-1059 R1, except as specified in paragraph (i)(2) of this AD.
Do all applicable related investigative and corrective actions
before further flight. Repeat the inspection of the horizontal
stabilizer lower skin, if applicable, thereafter at the applicable
intervals specified in paragraph 1.E., ``Compliance,'' of SASB 737-
55-1059 R1. Options specified in SASB 737-55-1059 R1 for
accomplishing the inspections are acceptable for the corresponding
requirements of this paragraph provided that the inspections are
done at the applicable times in paragraph 1.E., ``Compliance,'' of
the SASB 737-55-1059 R1.
(h) Inspections, Related Investigative Actions, and Corrective Actions
for Configuration 2 Horizontal Stabilizers on Group 1 Airplanes
For any Configuration 2 horizontal stabilizer on Group 1
airplanes, as identified in SASB 737-55-1059 R1: Except as specified
in paragraph (i)(1) of this AD, at the applicable time specified in
paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1, do the
actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this
AD; and do all applicable related investigative and corrective
actions; in accordance with the Accomplishment Instructions of SASB
737-55-1059 R1, except as specified in paragraph (i)(2) of this AD.
Do all applicable related investigative and corrective actions
before further flight. Repeat the inspections specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this AD, if applicable,
thereafter at the applicable intervals specified in paragraph 1.E.,
``Compliance,'' of SASB 737-55-1059 R1. Options specified in SASB
737-55-1059 R1, for accomplishing the inspections are acceptable for
the corresponding requirements of this paragraph provided that the
inspections are done at the applicable times in paragraph 1.E.,
``Compliance,'' of SASB 737-55-1059 R1.
(1) Do a high frequency eddy current inspection for cracking of
the skin around any repair common to the rear spar lower chord
between station (STA) 83.50 and STA 249.10 which was done as
specified in the structural repair manual or any external doubler
repair, and a detailed inspection for any loose or any missing
fastener of repaired doublers, except as specified in paragraph
(i)(3) of this AD.
(2) Do a detailed inspection for cracking of the inspar lower
skin between STA 83.50 and STA 249.10, except in areas repaired
common to the rear spar lower chord.
(3) Do a low frequency eddy current inspection for cracking of
the forward fastener row of any external doubler repair common to
the rear spar lower chord between STA 83.50 and STA 249.10.
(i) Service Information Exceptions
(1) Where SASB 737-55-1059 R1 specifies a compliance time
``after the Revision 1 date of this service bulletin,'' this AD
requires compliance within the specified compliance time after the
effective date of this AD.
(2) If any cracking, corrosion, hole elongation, or loose or
missing fastener is found during any inspection required by this AD,
and SASB 737-55-1059 R1 specifies to contact Boeing for repair
instructions: Before further flight, repair the cracking, corrosion,
hole elongation, loose or missing fasteners using a method approved
in accordance with the procedures specified in paragraph (j) of this
AD.
(3) Where SASB 737-55-1059 R1 specifies that doublers installed
with solid rivets do not need to be inspected for loose or missing
fasteners, this AD does not require doublers installed with solid
rivets or Hi-lok fasteners to be inspected for loose or missing
fasteners.
(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) 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.
(k) Related Information
For more information about this AD, contact George Garrido,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5232; fax: 562-627-5210; email: george.garrido@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Special Attention Service Bulletin 737-55-1059,
Revision 1, dated April 6, 2016.
(ii) Reserved.
(3) For Boeing service information identified in this AD,
contact Boeing
[[Page 15287]]
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.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 16, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-05768 Filed 3-27-17; 8:45 am]
BILLING CODE 4910-13-P