Airworthiness Directives; The Boeing Company Airplanes, 10855-10859 [2017-03112]
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10855
Rules and Regulations
Federal Register
Vol. 82, No. 31
Thursday, February 16, 2017
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF AGRICULTURE
Animal and Plant Health Inspection
Service
7 CFR Part 331
9 CFR Part 121
[Docket No. APHIS–2014–0095]
RIN 0579–AE08
Agricultural Bioterrorism Protection
Act of 2002; Biennial Review and
Republication of the Select Agent and
Toxin List; Amendments to the Select
Agent and Toxin Regulations; Delay of
Effective Date
Authority: 7 U.S.C. 8401; 7 CFR 2.22, 2.80,
and 371.3.
Animal and Plant Health
Inspection Service, USDA.
ACTION: Final rule; delay of effective
date.
AGENCY:
On January 19, 2017, we
published a final rule amending the
select agent and toxin regulations in
several ways, including the addition of
provisions to address the inactivation of
select agents, provisions addressing
biocontainment and biosafety, and
clarification of regulatory language
concerning security, training, incident
response, and records. In this document,
we are delaying the effective date of that
final rule.
DATES: The effective date of the final
rule published on January 19, 2017 (82
FR 6197), is delayed until March 21,
2017.
FOR FURTHER INFORMATION CONTACT: Mr.
Stephen O’Neill, Chief, Regulatory
Analysis and Development, PPD,
APHIS, 4700 River Road Unit 118,
Riverdale, MD 20737–1234; (301) 851–
3175.
SUPPLEMENTARY INFORMATION: On
January 19, 2017, the Animal and Plant
Health Inspection Service (APHIS)
published a final rule (82 FR 6197–
6210) to amend the select agent and
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SUMMARY:
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toxin regulations in several ways,
including the addition of provisions to
address the inactivation of select agents,
provisions addressing biocontainment
and biosafety, and clarification of
regulatory language concerning security,
training, incident response, and records.
In this document, we are delaying the
effective date until March 21, 2017, in
accordance with guidance issued
January 20, 2017, intended to provide
the new Administration an adequate
opportunity to review new and pending
regulations.
To the extent that 5 U.S.C. 553(b)(A)
applies to this action, it is exempt from
notice and comment for good cause and
the reasons cited above. APHIS finds
that notice and solicitation of comment
regarding the brief extension of the
effective date for the final regulation are
impracticable, unnecessary, or contrary
to the public interest pursuant to 5
U.S.C. 553(b)(B). APHIS also believes
that affected entities need to be
informed as soon as possible of the
extension and its length in order to plan
and adjust their implementation process
accordingly.
Done in Washington, DC, this 10th day of
February 2017.
Michael C. Gregoire,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. 2017–03125 Filed 2–15–17; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6430; Directorate
Identifier 2015–NM–176–AD; Amendment
39–18781; AD 2017–02–02]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2005–13–
30, for all The Boeing Company Model
737–100, –200, and –200C series
SUMMARY:
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airplanes. AD 2005–13–30 required
repetitive inspections to detect
discrepancies of certain fuselage skin
panels located just aft of the wheel well,
and repair if necessary. This new AD
adds new fuselage skin inspections for
cracking, inspections to detect missing
or loose fasteners and any disbonding or
cracking of bonded doublers, permanent
repairs of time-limited repairs, related
investigative and corrective actions if
necessary, and skin panel replacement.
This AD was prompted by an evaluation
by the design approval holder (DAH)
indicating that the fuselage skin is
subject to widespread fatigue damage
(WFD), and reports of cracks at the
chem-milled steps in the fuselage skin.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective March 23,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 23, 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–
6430.
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–
6430; 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
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New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–
5210; email: jennifer.tsakoumakis@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2005–13–30,
Amendment 39–14167 (70 FR 36829,
June 27, 2005) (‘‘AD 2005–13–30’’). AD
2005–13–30 applied to all Boeing Model
737–100, –200, and –200C series
airplanes. The NPRM published in the
Federal Register on May 11, 2016 (81
FR 29202) (‘‘the NPRM’’). The NPRM
was prompted by an evaluation by the
DAH indicating that the fuselage skin is
subject to WFD, and reports of cracks at
the chem-milled steps in the fuselage
skin. The NPRM proposed to require
fuselage skin inspections for cracking,
inspections to detect missing or loose
fasteners and any disbonding or
cracking of bonded doublers, permanent
repairs of time-limited repairs, related
investigative and corrective actions if
necessary, and skin panel replacement.
We are issuing this AD to detect and
correct fatigue cracking of the fuselage
skin panels, which could cause rapid
decompression 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.
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Request To Revise Compliance Time
Boeing requested that we revise
paragraph (i)(4) of the proposed AD to
specify that the exception to the service
information is for airplanes on which an
operator has a record that a skin panel
was replaced with a production skin
panel ‘‘before’’ 59,000 total flight cycles,
instead of ‘‘at or before’’ 59,000 total
flight cycles, because of limit of validity
(LOV) issues. Boeing also requested that
we revise the condition statement
regarding the time the skin panel was
replaced in paragraph (m) of the
proposed AD from ‘‘after’’ 59,000 total
flight cycles to ‘‘at or after’’ 59,000 total
flight cycles; and in paragraphs (m)(1)
and (m)(2) of the proposed AD from ‘‘at
or before’’ to ‘‘before.’’ Boeing explained
that if a skin panel is replaced at or after
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59,000 total flight cycles, no additional
safety inspections would be needed due
to the LOV. Boeing stated that upon
reaching the LOV the airplane will be
retired domestically and no longer
supported by Boeing.
Boeing also requested that we revise
the compliance time for the skin panel
replacement in paragraph (i)(4) of the
proposed AD to a time approved by the
FAA through the alternative method of
compliance (AMOC) process instead of
the time specified in the service
information. Boeing stated that since a
Boeing Commercial Airplanes
Organization Designation Authorization
(ODA) representative cannot approve
extensions to the compliance times
required by an AD, the AMOC approval
would have to come from the FAA.
We partially agree with Boeing’s
requests. We agree to change the
identification of the affected airplanes
as requested by Boeing in paragraphs
(i)(4), (m), (m)(1), and (m)(2) of this AD.
These changes will address the LOV
issues expressed by Boeing. We do not
agree with changing the compliance
time from the applicable time for the
next inspection as specified in the
service information. We have
determined that this is an appropriate
compliance time and provides an
acceptable level of safety. It also
provides operators with sufficient
information for maintenance planning
purposes.
Request To Revise Instructions for Skin
Panel Replacement
Boeing requested that we revise
paragraph (m) of the proposed AD,
which specifies replacing the applicable
skin panels and doing all applicable
related investigative and corrective
actions, with replacing the skin panels
in accordance with Part 8 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–
53–1065, Revision 3, dated June 30,
2015 (‘‘SASB 737–53–1065, R3’’).
We agree with replacing the skin
panels in accordance with Part 8 of the
Accomplishment Instructions of SASB
737–53–1065, R3. Part 8 of the
Accomplishment Instructions of SASB
737–53–1065, R3 adequately specifies
the required actions. We have revised
paragraph (m) of this AD accordingly.
Request To Add Service Information
Paragraph Part References
Boeing requested that we revise
paragraphs (j)(1)(ii), (j)(2)(ii), and (k) of
the proposed AD by adding the service
information paragraph part references.
Boeing stated that paragraph (h) of the
proposed AD includes the part
reference.
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We do not agree with Boeing’s
requests. Paragraph (h) of this AD, in
part, specifies the specific service
information paragraph reference for
doing repairs that are terminating action
for the repetitive inspections at the
repaired locations only. We determined
that this reference is needed for clarity.
We do not agree that the other
references are needed for clarity. We
have not changed this AD in this regard.
Request To Clarify Post-modification
Airworthiness Limitation Inspections
Boeing requested that we revise
paragraph (l) of the proposed AD to
specify that table 6 of paragraph 1.E.,
‘‘Compliance,’’ of SASB 737–53–1065,
R3 is for post-modification
airworthiness limitation inspections at
the modified locations. Boeing
explained that since airworthiness
limitation inspections are required by
maintenance and operational rules, it is
unnecessary to mandate them in this
AD.
We agree with Boeing’s request. We
have revised paragraph (l) of this AD
accordingly.
Request To Revise the NPRM To
Address Certain Repaired Areas
For airplanes subject to the
requirements of paragraph (h) of the
proposed AD, Boeing requested that we
add a paragraph that specifies that
inspections are not required in areas
that are spanned by an FAA-approved
repair that has met certain conditions.
Boeing submitted specific conditions.
Boeing stated that its request is to
address elimination of inspections for
repairs that have been accomplished for
damage other than chem-mill cracking.
We do not agree with Boeing’s
request. Paragraph (h) of this AD
specifies to do the applicable
inspections and related investigative
and corrective actions specified in the
Accomplishment Instructions of SASB
737–53–1065, R3. This service
information already contains the criteria
Boeing proposed. Therefore, the criteria
do not need to be repeated in this AD.
We have not changed this AD in this
regard.
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
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• 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 737–53–1065, R3.
The service information describes
procedures for inspection and repair of
the fuselage skin panels between body
station (BS) 727 and BS 1016, and
between stringers S–14 and S–25; and
also describes procedures for skin panel
replacement. This service information is
10857
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 9
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection [actions retained from AD
2005–13–30].
Inspection [new action] .............................
Up to 88 work-hours × $85 per hour =
$7,480 per inspection cycle.
Up to 1,914 work-hours × $85 per hour =
$162,690 per inspection cycle.
$0
Skin panel replacement [new action] ........
688 work-hours × $85 per hour = $58,480
96,000
We estimate the following costs to do
any necessary repairs that will be
Parts cost
0
required based on the results of the
inspection. We have no way of
Cost on U.S.
operators
Cost per product
Up to $7,480 per inspection cycle.
Up to $162,690 per
inspection cycle.
$154,480 .................
Up to $67,320 per
inspection cycle.
Up to $1,464,210
per inspection
cycle.
$1,390,320.
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Time-limited repair ............................................................
Permanent repair ..............................................................
Permanent repair inspection .............................................
24 work-hours × $85 per hour = $2,040 ..........................
43 work-hours × $85 per hour = $3,655 ..........................
7 work-hours × $85 per hour = $595 ...............................
1 We
(1)
(1)
(1)
Cost per
product
1 $2,040
1 3,655
1 595
have received no definitive data that will enable us to provide parts cost estimates for the on-condition actions specified in this AD.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
Authority for This Rulemaking
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Parts cost
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
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products identified in this rulemaking
action.
Regulatory Findings
We have determined that 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.
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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
removing Airworthiness Directive (AD)
2005–13–30, Amendment 39–14167 (70
FR 36829, June 27, 2005), and adding
the following new AD:
■
2017–02–02 The Boeing Company:
Amendment 39–18781; Docket No.
FAA–2016–6430; Directorate Identifier
2015–NM–176–AD.
(a) Effective Date
This AD is effective March 23, 2017.
(b) Affected ADs
This AD replaces AD 2005–13–30,
Amendment 39–14167 (70 FR 36829, June
27, 2005) (‘‘AD 2005–13–30’’).
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(c) Applicability
This AD applies to all The Boeing
Company Model 737–100, –200, and –200C
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 an evaluation by
the design approval holder indicating that
the fuselage skin is subject to widespread
fatigue damage, and reports of cracks at the
chem-milled steps in the fuselage skin. We
are issuing this AD to detect and correct
fatigue cracking of the fuselage skin panels,
which could cause rapid decompression of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Actions for Group 1 Airplanes
For Group 1 airplanes identified in Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015
(‘‘SASB 737–53–1065, R3’’): Within 120 days
after the effective date of this AD, accomplish
actions to correct the unsafe condition (e.g.,
inspections, repairs, modifications, and
related investigative and corrective actions)
using a method approved in accordance with
the procedures specified in paragraph (o) of
this AD.
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(h) Inspections, Related Investigative and
Corrective Actions
Except for Group 1 airplanes identified in
SASB 737–53–1065, R3: At the applicable
times specified in tables 1 and 2 of paragraph
1.E., ‘‘Compliance,’’ of SASB 737–53–1065,
R3, except as required by paragraphs (i)(1)
and (i)(2) of this AD, do the applicable
inspections to detect cracks in the fuselage
skin panels; and do all applicable related
investigative and corrective actions; in
accordance with the Accomplishment
Instructions of SASB 737–53–1065, R3,
except as required by paragraphs (i)(3) and
(i)(4) of this AD. Do all applicable related
investigative and corrective actions before
further flight. Repeat the applicable
inspections thereafter at the applicable
intervals specified in SASB 737–53–1065,
R3. Accomplishment of a repair in
accordance with ‘‘Part 3: Repair’’ of the
Accomplishment Instructions of SASB 737–
53–1065, R3, except as required by paragraph
(i)(3) of this AD, is terminating action for the
repetitive inspections required by this
paragraph at the repaired locations only.
(i) Exceptions to SASB 737–53–1065, R3
(1) Where SASB 737–53–1065, R3 specifies
compliance times ‘‘after the Revision 3 date
of this service bulletin,’’ this AD requires
compliance within the specified compliance
times after the effective date of this AD.
(2) The Condition column of paragraph
1.E., ‘‘Compliance,’’ of SASB 737–53–1065,
R3 refers to airplanes in certain
configurations as of the ‘‘issue date of
Revision 3 of this service bulletin.’’ However,
this AD applies to airplanes in the specified
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configurations ‘‘as of the effective date of this
AD.’’
(3) Where SASB 737–53–1065, R3 specifies
contacting Boeing for repair instructions or
work instructions, before further flight, repair
or perform the work instructions using a
method approved in accordance with the
procedures specified in paragraph (o) of this
AD, except as required by paragraph (i)(4) of
this AD.
(4) For airplanes on which an operator has
a record that a skin panel was replaced with
a production skin panel before 59,000 total
flight cycles: At the applicable time for the
next inspection as specified in tables 1 and
2 of paragraph 1.E., ‘‘Compliance,’’ of SASB
737–53–1065, R3, except as provided by
paragraphs (i)(1) and (i)(2) of this AD,
perform inspections and applicable
corrective actions using a method approved
in accordance with the procedures specified
in paragraph (o) of this AD.
the Accomplishment Instructions of SASB
737–53–1065, R3, except as required by
paragraph (i)(3) of this AD. Do all applicable
related investigative and corrective actions
before further flight. Repeat the applicable
inspections thereafter at the applicable
intervals specified in SASB 737–53–1065,
R3.
(ii) Make the time limited repair
permanent; and do all applicable related
investigative and corrective actions; in
accordance the Accomplishment Instructions
of SASB 737–53–1065, R3, except as required
by paragraph (i)(3) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
Accomplishing the permanent repair
required by this paragraph terminates the
inspections required by paragraph (j)(2)(i) of
this AD for the permanently repaired area
only.
(j) Actions for Airplanes With a Time
Limited Repair Installed
Except for Group 1 airplanes identified in
SASB 737–53–1065, R3: Do the applicable
actions required by paragraphs (j)(1) and
(j)(2) of this AD.
(1) For airplanes with a time limited repair
installed as specified in Boeing Special
Attention Service Bulletin 737–53–1065,
Revision 2, dated April 19, 2001: At the
applicable times specified in table 3 of
paragraph 1.E., ‘‘Compliance,’’ of SASB 737–
53–1065, R3, except as provided by
paragraphs (i)(1) and (i)(2) of this AD, do the
actions specified in paragraphs (j)(1)(i) and
(j)(1)(ii) of this AD.
(i) Do the applicable inspections to detect
missing or loose fasteners and any
disbonding or cracking of bonded doublers;
and do all applicable related investigative
and corrective actions; in accordance with
the Accomplishment Instructions of SASB
737–53–1065, R3, except as required by
paragraph (i)(3) of this AD. Do all applicable
related investigative and corrective actions
before further flight. Repeat the applicable
inspections thereafter at the applicable
intervals specified in SASB 737–53–1065,
R3.
(ii) Make the time limited repair
permanent; and do all applicable related
investigative and corrective actions; in
accordance the Accomplishment Instructions
of SASB 737–53–1065, R3, except as required
by paragraph (i)(3) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
Accomplishing the permanent repair
required by this paragraph terminates the
inspections required by paragraph (j)(1)(i) of
this AD for the permanently repaired area
only.
(2) For airplanes with a time limited repair
installed as specified in SASB 737–53–1065,
R3: At the applicable times specified in table
4 of paragraph 1.E., ‘‘Compliance,’’ of SASB
737–53–1065, R3, do the actions specified in
paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) Do the applicable inspections to detect
missing or loose fasteners and any
disbonding or cracking of bonded doublers;
and do all applicable related investigative
and corrective actions; in accordance with
(l) Post-Modification Inspections
Table 6 of paragraph 1.E., ‘‘Compliance,’’
of SASB 737–53–1065, R3 specifies postmodification airworthiness limitation
inspections in compliance with 14 CFR
25.571(a)(3) at the modified locations, which
support compliance with 14 CFR
121.1109(c)(2) or 129.109(b)(2). As
airworthiness limitations, these inspections
are required by maintenance and operational
rules. It is therefore unnecessary to mandate
them in this AD. Deviations from these
inspections require FAA approval, but do not
require an alternative method of compliance.
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(k) Modification of Certain Permanent
Repairs
Except for Group 1 airplanes identified in
SASB 737–53–1065, R3: For airplanes with
an existing time limited repair that was made
permanent as specified in Boeing Special
Attention Service Bulletin 737–53–1065,
Revision 2, dated April 19, 2001, at the
applicable times specified in table 5 of
paragraph 1.E., ‘‘Compliance,’’ of SASB 737–
53–1065, R3, except as required by paragraph
(i)(1) of this AD, modify the existing
permanent repair; and do all applicable
related investigative and corrective actions;
in accordance the Accomplishment
Instructions of SASB 737–53–1065, R3,
except as required by paragraph (i)(3) of this
AD. Do all applicable related investigative
and corrective actions before further flight.
(m) Skin Panel Replacement
Except for Group 1 airplanes identified in
SASB 737–53–1065, R3: At the later of the
times specified in paragraphs (m)(1) and
(m)(2) of this AD, replace the applicable skin
panels, in accordance with the Part 8 of the
Accomplishment Instructions of SASB 737–
53–1065, R3. Doing the skin panel
replacement required by this paragraph
terminates the inspection requirements of
paragraph (h) of this AD for that skin panel
only, provided the skin panel was replaced
with a production skin panel at or after
59,000 total flight cycles.
(1) Before 60,000 total flight cycles, but not
before 59,000 total flight cycles.
(2) Within 6,000 flight cycles after the
effective date of this AD, but not before
59,000 total flight cycles.
E:\FR\FM\16FER1.SGM
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Federal Register / Vol. 82, No. 31 / Thursday, February 16, 2017 / Rules and Regulations
(n) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Special
Attention Service Bulletin 737–53–1065,
Revision 2, dated April 19, 2001, which was
incorporated by reference in AD 2005–13–30.
(o) 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 (p) 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) AMOCs approved previously for AD
2005–13–30, are approved as AMOCs for the
corresponding provisions of paragraph (h) of
this AD.
jstallworth on DSK7TPTVN1PROD with RULES
(p) Related Information
For more information about this AD,
contact Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles ACO, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–5210;
email: jennifer.tsakoumakis@faa.gov.
(q) 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 737–53–1065, Revision 3, dated June
30, 2015.
(ii) Reserved.
(3) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS), 2600
Westminster Blvd., MC 110–SK57, Seal
Beach, CA 90740–5600; telephone 562–797–
1717; Internet https://
www.myboeingfleet.com.
VerDate Sep<11>2014
11:26 Feb 15, 2017
Jkt 241001
(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 January
11, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–03112 Filed 2–15–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–7003; Directorate
Identifier 2016–CE–015–AD; Amendment
39–18766; AD 2016–26–08]
RIN 2120–AA64
Airworthiness Directives; PILATUS
AIRCRAFT LTD. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
The FAA is correcting an
airworthiness directive (AD) that
published in the Federal Register. That
AD applies to all PILATUS AIRCRAFT
LTD. Models PC–12, PC–12/45, PC–12/
47, and PC–12/47E airplanes. The
second reference to the main landing
gear (MLG) in paragraph (f)(6) is
incorrect. This document corrects that
error. In all other respects, the original
document remains the same; however
we are publishing the entire rule in the
Federal Register.
DATES: This final rule is effective
February 16, 2017. The effective date of
AD 2016–26–08 remains February 9,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 9, 2017 (82 FR 1172,
January 5, 2017).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
7003; 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
SUMMARY:
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
10859
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document 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:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090; email:
doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
Airworthiness Directive 2016–26–08,
Amendment 39–18766 (82 FR 1172,
January 5, 2017), requires incorporating
new revisions into the Limitations
section, Chapter 4, of the FAA-approved
maintenance program (e.g., maintenance
manual). The limitations were revised to
include repetitive inspections of the
main landing gear (MLG) attachment
bolts.
As published, in paragraph (f)(6) there
is a typographical error to the second
reference of the MLG. The published
reference is MLB and it is should be
MLG.
Although no other part of the
preamble or regulatory information has
been corrected, we are publishing the
entire rule in the Federal Register.
The effective date of this AD remains
February 9, 2017.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Correction
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
[Corrected]
2. The FAA amends § 39.13 by
removing 39–18005 (79 FR 67343,
November 13, 2014) and adding the
following new AD:
■
2016–26–08 PILATUS AIRCRAFT LTD.:
Amendment 39–18766; Docket No.
FAA–2016–7003; Directorate Identifier
2016–CE–015–AD.
E:\FR\FM\16FER1.SGM
16FER1
]]>Agencies
[Federal Register Volume 82, Number 31 (Thursday, February 16, 2017)]
[Rules and Regulations]
[Pages 10855-10859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03112]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6430; Directorate Identifier 2015-NM-176-AD;
Amendment 39-18781; AD 2017-02-02]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2005-13-30,
for all The Boeing Company Model 737-100, -200, and -200C series
airplanes. AD 2005-13-30 required repetitive inspections to detect
discrepancies of certain fuselage skin panels located just aft of the
wheel well, and repair if necessary. This new AD adds new fuselage skin
inspections for cracking, inspections to detect missing or loose
fasteners and any disbonding or cracking of bonded doublers, permanent
repairs of time-limited repairs, related investigative and corrective
actions if necessary, and skin panel replacement. This AD was prompted
by an evaluation by the design approval holder (DAH) indicating that
the fuselage skin is subject to widespread fatigue damage (WFD), and
reports of cracks at the chem-milled steps in the fuselage skin. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective March 23, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 23,
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-
6430.
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-
6430; 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
[[Page 10856]]
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email:
jennifer.tsakoumakis@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2005-13-30, Amendment 39-14167 (70 FR 36829,
June 27, 2005) (``AD 2005-13-30''). AD 2005-13-30 applied to all Boeing
Model 737-100, -200, and -200C series airplanes. The NPRM published in
the Federal Register on May 11, 2016 (81 FR 29202) (``the NPRM''). The
NPRM was prompted by an evaluation by the DAH indicating that the
fuselage skin is subject to WFD, and reports of cracks at the chem-
milled steps in the fuselage skin. The NPRM proposed to require
fuselage skin inspections for cracking, inspections to detect missing
or loose fasteners and any disbonding or cracking of bonded doublers,
permanent repairs of time-limited repairs, related investigative and
corrective actions if necessary, and skin panel replacement. We are
issuing this AD to detect and correct fatigue cracking of the fuselage
skin panels, which could cause rapid decompression 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 Revise Compliance Time
Boeing requested that we revise paragraph (i)(4) of the proposed AD
to specify that the exception to the service information is for
airplanes on which an operator has a record that a skin panel was
replaced with a production skin panel ``before'' 59,000 total flight
cycles, instead of ``at or before'' 59,000 total flight cycles, because
of limit of validity (LOV) issues. Boeing also requested that we revise
the condition statement regarding the time the skin panel was replaced
in paragraph (m) of the proposed AD from ``after'' 59,000 total flight
cycles to ``at or after'' 59,000 total flight cycles; and in paragraphs
(m)(1) and (m)(2) of the proposed AD from ``at or before'' to
``before.'' Boeing explained that if a skin panel is replaced at or
after 59,000 total flight cycles, no additional safety inspections
would be needed due to the LOV. Boeing stated that upon reaching the
LOV the airplane will be retired domestically and no longer supported
by Boeing.
Boeing also requested that we revise the compliance time for the
skin panel replacement in paragraph (i)(4) of the proposed AD to a time
approved by the FAA through the alternative method of compliance (AMOC)
process instead of the time specified in the service information.
Boeing stated that since a Boeing Commercial Airplanes Organization
Designation Authorization (ODA) representative cannot approve
extensions to the compliance times required by an AD, the AMOC approval
would have to come from the FAA.
We partially agree with Boeing's requests. We agree to change the
identification of the affected airplanes as requested by Boeing in
paragraphs (i)(4), (m), (m)(1), and (m)(2) of this AD. These changes
will address the LOV issues expressed by Boeing. We do not agree with
changing the compliance time from the applicable time for the next
inspection as specified in the service information. We have determined
that this is an appropriate compliance time and provides an acceptable
level of safety. It also provides operators with sufficient information
for maintenance planning purposes.
Request To Revise Instructions for Skin Panel Replacement
Boeing requested that we revise paragraph (m) of the proposed AD,
which specifies replacing the applicable skin panels and doing all
applicable related investigative and corrective actions, with replacing
the skin panels in accordance with Part 8 of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 737-53-1065,
Revision 3, dated June 30, 2015 (``SASB 737-53-1065, R3'').
We agree with replacing the skin panels in accordance with Part 8
of the Accomplishment Instructions of SASB 737-53-1065, R3. Part 8 of
the Accomplishment Instructions of SASB 737-53-1065, R3 adequately
specifies the required actions. We have revised paragraph (m) of this
AD accordingly.
Request To Add Service Information Paragraph Part References
Boeing requested that we revise paragraphs (j)(1)(ii), (j)(2)(ii),
and (k) of the proposed AD by adding the service information paragraph
part references. Boeing stated that paragraph (h) of the proposed AD
includes the part reference.
We do not agree with Boeing's requests. Paragraph (h) of this AD,
in part, specifies the specific service information paragraph reference
for doing repairs that are terminating action for the repetitive
inspections at the repaired locations only. We determined that this
reference is needed for clarity. We do not agree that the other
references are needed for clarity. We have not changed this AD in this
regard.
Request To Clarify Post-modification Airworthiness Limitation
Inspections
Boeing requested that we revise paragraph (l) of the proposed AD to
specify that table 6 of paragraph 1.E., ``Compliance,'' of SASB 737-53-
1065, R3 is for post-modification airworthiness limitation inspections
at the modified locations. Boeing explained that since airworthiness
limitation inspections are required by maintenance and operational
rules, it is unnecessary to mandate them in this AD.
We agree with Boeing's request. We have revised paragraph (l) of
this AD accordingly.
Request To Revise the NPRM To Address Certain Repaired Areas
For airplanes subject to the requirements of paragraph (h) of the
proposed AD, Boeing requested that we add a paragraph that specifies
that inspections are not required in areas that are spanned by an FAA-
approved repair that has met certain conditions. Boeing submitted
specific conditions. Boeing stated that its request is to address
elimination of inspections for repairs that have been accomplished for
damage other than chem-mill cracking.
We do not agree with Boeing's request. Paragraph (h) of this AD
specifies to do the applicable inspections and related investigative
and corrective actions specified in the Accomplishment Instructions of
SASB 737-53-1065, R3. This service information already contains the
criteria Boeing proposed. Therefore, the criteria do not need to be
repeated in this AD. We have not changed this AD in this regard.
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
[[Page 10857]]
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 737-53-1065, R3. The service information describes
procedures for inspection and repair of the fuselage skin panels
between body station (BS) 727 and BS 1016, and between stringers S-14
and S-25; and also describes procedures for skin panel replacement.
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 9 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 [actions retained from Up to 88 work-hours x $0 Up to $7,480 per Up to $67,320 per
AD 2005-13-30]. $85 per hour = $7,480 inspection cycle. inspection cycle.
per inspection cycle.
Inspection [new action].......... Up to 1,914 work-hours x 0 Up to $162,690 per Up to $1,464,210
$85 per hour = $162,690 inspection cycle. per inspection
per inspection cycle. cycle.
Skin panel replacement [new 688 work-hours x $85 per 96,000 $154,480........... $1,390,320.
action]. hour = $58,480.
----------------------------------------------------------------------------------------------------------------
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 Cost per
Action Labor cost cost product
----------------------------------------------------------------------------------------------------------------
Time-limited repair........................... 24 work-hours x $85 per hour = $2,040 (\1\) \1\ $2,040
Permanent repair.............................. 43 work-hours x $85 per hour = $3,655 (\1\) \1\ 3,655
Permanent repair inspection................... 7 work-hours x $85 per hour = $595... (\1\) \1\ 595
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that will enable us to provide parts cost estimates for the on-condition
actions specified in this AD.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that 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.
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 removing Airworthiness Directive (AD)
2005-13-30, Amendment 39-14167 (70 FR 36829, June 27, 2005), and adding
the following new AD:
2017-02-02 The Boeing Company: Amendment 39-18781; Docket No. FAA-
2016-6430; Directorate Identifier 2015-NM-176-AD.
(a) Effective Date
This AD is effective March 23, 2017.
(b) Affected ADs
This AD replaces AD 2005-13-30, Amendment 39-14167 (70 FR 36829,
June 27, 2005) (``AD 2005-13-30'').
[[Page 10858]]
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200,
and -200C 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 an evaluation by the design approval
holder indicating that the fuselage skin is subject to widespread
fatigue damage, and reports of cracks at the chem-milled steps in
the fuselage skin. We are issuing this AD to detect and correct
fatigue cracking of the fuselage skin panels, which could cause
rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Actions for Group 1 Airplanes
For Group 1 airplanes identified in Boeing Special Attention
Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015
(``SASB 737-53-1065, R3''): Within 120 days after the effective date
of this AD, accomplish actions to correct the unsafe condition
(e.g., inspections, repairs, modifications, and related
investigative and corrective actions) using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD.
(h) Inspections, Related Investigative and Corrective Actions
Except for Group 1 airplanes identified in SASB 737-53-1065, R3:
At the applicable times specified in tables 1 and 2 of paragraph
1.E., ``Compliance,'' of SASB 737-53-1065, R3, except as required by
paragraphs (i)(1) and (i)(2) of this AD, do the applicable
inspections to detect cracks in the fuselage skin panels; and do all
applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of SASB 737-53-1065,
R3, except as required by paragraphs (i)(3) and (i)(4) of this AD.
Do all applicable related investigative and corrective actions
before further flight. Repeat the applicable inspections thereafter
at the applicable intervals specified in SASB 737-53-1065, R3.
Accomplishment of a repair in accordance with ``Part 3: Repair'' of
the Accomplishment Instructions of SASB 737-53-1065, R3, except as
required by paragraph (i)(3) of this AD, is terminating action for
the repetitive inspections required by this paragraph at the
repaired locations only.
(i) Exceptions to SASB 737-53-1065, R3
(1) Where SASB 737-53-1065, R3 specifies compliance times
``after the Revision 3 date of this service bulletin,'' this AD
requires compliance within the specified compliance times after the
effective date of this AD.
(2) The Condition column of paragraph 1.E., ``Compliance,'' of
SASB 737-53-1065, R3 refers to airplanes in certain configurations
as of the ``issue date of Revision 3 of this service bulletin.''
However, this AD applies to airplanes in the specified
configurations ``as of the effective date of this AD.''
(3) Where SASB 737-53-1065, R3 specifies contacting Boeing for
repair instructions or work instructions, before further flight,
repair or perform the work instructions using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD, except as required by paragraph (i)(4) of this AD.
(4) For airplanes on which an operator has a record that a skin
panel was replaced with a production skin panel before 59,000 total
flight cycles: At the applicable time for the next inspection as
specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' of
SASB 737-53-1065, R3, except as provided by paragraphs (i)(1) and
(i)(2) of this AD, perform inspections and applicable corrective
actions using a method approved in accordance with the procedures
specified in paragraph (o) of this AD.
(j) Actions for Airplanes With a Time Limited Repair Installed
Except for Group 1 airplanes identified in SASB 737-53-1065, R3:
Do the applicable actions required by paragraphs (j)(1) and (j)(2)
of this AD.
(1) For airplanes with a time limited repair installed as
specified in Boeing Special Attention Service Bulletin 737-53-1065,
Revision 2, dated April 19, 2001: At the applicable times specified
in table 3 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1065,
R3, except as provided by paragraphs (i)(1) and (i)(2) of this AD,
do the actions specified in paragraphs (j)(1)(i) and (j)(1)(ii) of
this AD.
(i) Do the applicable inspections to detect missing or loose
fasteners and any disbonding or cracking of bonded doublers; and do
all applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of SASB 737-53-1065,
R3, except as required by paragraph (i)(3) of this AD. Do all
applicable related investigative and corrective actions before
further flight. Repeat the applicable inspections thereafter at the
applicable intervals specified in SASB 737-53-1065, R3.
(ii) Make the time limited repair permanent; and do all
applicable related investigative and corrective actions; in
accordance the Accomplishment Instructions of SASB 737-53-1065, R3,
except as required by paragraph (i)(3) of this AD. Do all applicable
related investigative and corrective actions before further flight.
Accomplishing the permanent repair required by this paragraph
terminates the inspections required by paragraph (j)(1)(i) of this
AD for the permanently repaired area only.
(2) For airplanes with a time limited repair installed as
specified in SASB 737-53-1065, R3: At the applicable times specified
in table 4 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1065,
R3, do the actions specified in paragraphs (j)(2)(i) and (j)(2)(ii)
of this AD.
(i) Do the applicable inspections to detect missing or loose
fasteners and any disbonding or cracking of bonded doublers; and do
all applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of SASB 737-53-1065,
R3, except as required by paragraph (i)(3) of this AD. Do all
applicable related investigative and corrective actions before
further flight. Repeat the applicable inspections thereafter at the
applicable intervals specified in SASB 737-53-1065, R3.
(ii) Make the time limited repair permanent; and do all
applicable related investigative and corrective actions; in
accordance the Accomplishment Instructions of SASB 737-53-1065, R3,
except as required by paragraph (i)(3) of this AD. Do all applicable
related investigative and corrective actions before further flight.
Accomplishing the permanent repair required by this paragraph
terminates the inspections required by paragraph (j)(2)(i) of this
AD for the permanently repaired area only.
(k) Modification of Certain Permanent Repairs
Except for Group 1 airplanes identified in SASB 737-53-1065, R3:
For airplanes with an existing time limited repair that was made
permanent as specified in Boeing Special Attention Service Bulletin
737-53-1065, Revision 2, dated April 19, 2001, at the applicable
times specified in table 5 of paragraph 1.E., ``Compliance,'' of
SASB 737-53-1065, R3, except as required by paragraph (i)(1) of this
AD, modify the existing permanent repair; and do all applicable
related investigative and corrective actions; in accordance the
Accomplishment Instructions of SASB 737-53-1065, R3, except as
required by paragraph (i)(3) of this AD. Do all applicable related
investigative and corrective actions before further flight.
(l) Post-Modification Inspections
Table 6 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1065,
R3 specifies post-modification airworthiness limitation inspections
in compliance with 14 CFR 25.571(a)(3) at the modified locations,
which support compliance with 14 CFR 121.1109(c)(2) or
129.109(b)(2). As airworthiness limitations, these inspections are
required by maintenance and operational rules. It is therefore
unnecessary to mandate them in this AD. Deviations from these
inspections require FAA approval, but do not require an alternative
method of compliance.
(m) Skin Panel Replacement
Except for Group 1 airplanes identified in SASB 737-53-1065, R3:
At the later of the times specified in paragraphs (m)(1) and (m)(2)
of this AD, replace the applicable skin panels, in accordance with
the Part 8 of the Accomplishment Instructions of SASB 737-53-1065,
R3. Doing the skin panel replacement required by this paragraph
terminates the inspection requirements of paragraph (h) of this AD
for that skin panel only, provided the skin panel was replaced with
a production skin panel at or after 59,000 total flight cycles.
(1) Before 60,000 total flight cycles, but not before 59,000
total flight cycles.
(2) Within 6,000 flight cycles after the effective date of this
AD, but not before 59,000 total flight cycles.
[[Page 10859]]
(n) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD using Boeing Special Attention Service
Bulletin 737-53-1065, Revision 2, dated April 19, 2001, which was
incorporated by reference in AD 2005-13-30.
(o) 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 (p) 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) AMOCs approved previously for AD 2005-13-30, are approved as
AMOCs for the corresponding provisions of paragraph (h) of this AD.
(p) Related Information
For more information about this AD, contact Jennifer
Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5264; fax: 562-627-5210; email:
jennifer.tsakoumakis@faa.gov.
(q) 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 737-53-1065,
Revision 3, dated June 30, 2015.
(ii) Reserved.
(3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com.
(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 January 11, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-03112 Filed 2-15-17; 8:45 am]
BILLING CODE 4910-13-P
