Airworthiness Directives; The Boeing Company Airplanes, 24468-24472 [2017-10288]
Download as PDF
24468
Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Rules and Regulations
(i) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2016–0224, dated
November 9, 2016, for related information.
The MCAI can be found in the AD docket on
the Internet at: https://www.regulations.gov/
document?D=FAA-2017-0053-0002.
(j) 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) British Aerospace Jetstream Series 3100
& 3200 Service Bulletin 32–A–JA851226,
Revision 7, dated May 25, 2015.
(ii) Heroux Devtek Service Bulletin 32–19,
Revision 7, dated March 16, 2015.
(3) For British Aerospace Regional Aircraft
service information identified in this AD,
contact BAE Systems (Operations) Ltd,
Customer Information Department, Prestwick
International Airport, Ayrshire, KA9 2RW,
Scotland, United Kingdom; phone: +44 1292
675207, fax: +44 1292 675704; email:
RApublications@baesystems.com; Internet:
https://www.jetstreamcentral.com.
(4) You may review copies of the
referenced service information at the FAA,
Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148. In addition, you
can access this service information on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2017–0053.
(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 Kansas City, Missouri, on May
10, 2017.
Melvin Johnson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–10408 Filed 5–26–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
sradovich on DSK3GMQ082PROD with RULES
14 CFR Part 39
[Docket No. FAA–2016–6667; Directorate
Identifier 2015–NM–125–AD; Amendment
39–18882; AD 2017–10–08]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
VerDate Sep<11>2014
17:28 May 26, 2017
Jkt 241001
ACTION:
Final rule.
We are superseding
Airworthiness Directive (AD) 2009–21–
01 for certain The Boeing Company
Model 737–300 and 737–400 series
airplanes. AD 2009–21–01 required
repetitive inspections to detect cracking
of the aft fuselage skin, and related
investigative and corrective actions if
necessary. This new AD adds certain
inspections, repairs, replacement,
related investigative and corrective
actions if necessary; and removes
certain airplanes from the applicability.
This AD was prompted by an evaluation
by the design approval holder (DAH)
indicating that the aft fuselage skin is
subject to widespread fatigue damage
(WFD), and by reports of aft fuselage
cracking. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
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
This AD is effective July 5, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 5, 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–
6667.
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009–21–01,
Amendment 39–16038 (74 FR 52395,
October 13, 2009) (‘‘AD 2009–21–01’’).
AD 2009–21–01 applied to certain the
Boeing Company Model 737–300 and
737–400 series airplanes. The NPRM
published in the Federal Register on
May 13, 2016 (81 FR 29802). The NPRM
was prompted by an evaluation by the
DAH indicating that the aft fuselage skin
is subject to WFD, and by reports of aft
fuselage cracking. The NPRM proposed
to continue to require repetitive
inspections to detect cracking of the aft
fuselage skin, and related investigative
and corrective actions if necessary. The
NPRM also proposed to add new aft
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.
The NPRM also proposed to remove
Model 737–400 series airplanes from the
applicability. We are issuing this AD to
detect and correct cracking in the aft
fuselage skin along the longitudinal
edges of the chem-milled pockets in the
bonded skin doubler, which could
result in possible rapid decompression
and reduced structural integrity of the
airplane.
Examining the AD Docket
Comments
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6667; 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:
Jennifer Tsakoumakis, Aerospace
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.
DATES:
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
Request To Revise the Precipitating
Event Statement
Boeing requested that we revise the
precipitating event statement by
including that there have been reports of
aft fuselage cracking. Boeing stated that
this revision would be consistent with
wording of other related rulemaking.
We agree with Boeing’s request
because it provides additional clarity to
the precipitating event statement. We
have revised the SUMMARY and
Discussion sections, and paragraph (e)
of this AD accordingly.
E:\FR\FM\30MYR1.SGM
30MYR1
Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Rules and Regulations
Request To Require Reinstalling Lap
Joint Modification
Jet2.com Limited (Jet2) requested that
we revise the NPRM to require
reinstalling the lap joint modification
previously installed in accordance with
AD 2015–21–06, Amendment 39–18298
(80 FR 69839, November 12, 2015) (‘‘AD
2015–21–06’’), which requires the S–14
lap joint to be trimmed out prior to
50,000 total flight cycles. Jet2 stated that
Boeing Special Attention Service
Bulletin 737–53–1168, Revision 4, dated
June 3, 2015 (‘‘SASB 737–53–1168,
Revision 4’’) specifies reinstalling the
lap joint modification.
We do not agree with the commenter’s
request. The modification required in
AD 2015–21–06 consists of trimming
out the lap splice, such that if this
modification were installed, it would be
impossible to install a new skin without
reinstalling the lap modification. If the
instructions in SASB 737–53–1168,
Revision 4, to reinstall the lap splice
modification were accidently
overlooked, it would become clear to
the installer that the reinstallation
would be required. We have not
changed this AD in this regard.
Request To Address Certain Repairs
Boeing requested that we add a
paragraph to the proposed AD to
address repairs that are installed on the
airplane for reasons other than chemmill cracking. Boeing submitted
suggested language and pointed out that
the additional language is similar to that
in other rulemaking.
We disagree with Boeing’s request.
Part 1 of the Accomplishment
Instructions of SASB 737–53–1168,
Revision 4, does not make a distinction
regarding why an existing repair was
installed. Therefore, repairs installed for
damage other than a chem-mill crack are
already addressed. We have not changed
this AD in this regard.
sradovich on DSK3GMQ082PROD with RULES
Request To Revise Proposed
Compliance Time
Boeing requested that we revise
paragraph (h)(4) of the proposed AD to
do the actions at an initial compliance
time obtained through the alternative
method of compliance (AMOC) process
specified in paragraph (n)(1) of the
proposed AD. Boeing stated that the
repetitive inspections would still be
done at the times specified in the
service information. Boeing also
requested that we include in the
paragraph revision the terminating
action of skin panel replacement at the
time approved through an AMOC.
Boeing stated that its request would
provide a reset on the compliance times
VerDate Sep<11>2014
17:28 May 26, 2017
Jkt 241001
if the skin panel was replaced prior to
53,000 total airplane cycles. Boeing
explained that its authorized
representative under the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA)
cannot approve extensions to the
compliance times.
We partially agree with Boeing’s
request. We agree that, for airplanes
with skin panels replaced prior to
53,000 total flight cycles, in order to
reset the inspection threshold on the
replaced skin panels, approval must
come from the FAA. Under the
provisions of paragraph (n) of this AD,
we may consider requests for a reset of
the compliance times if the skin panel
was replaced prior to 53,000 total
airplane cycles if data are submitted to
substantiate that such an adjustment
would provide an acceptable level of
safety. We have not changed this AD in
this regard.
Request To Specify the Service
Information Accomplishment
Instructions Part Numbers
Boeing requested that we add the
specific part of the accomplishment
instructions in paragraphs (i)(1)(ii),
(i)(2)(ii), and (j) of the proposed AD.
Boeing stated that paragraph (g) of the
proposed AD specifies the specific part
number, and that this change would
make these paragraphs consistent with
the wording in paragraph (g) of the
proposed AD.
We agree with Boeing’s request. We
agree that specifying the specific part of
the Accomplishment Instructions of
SASB 737–53–1168, Revision 4, will
add clarity to the AD. We have revised
paragraphs (i)(1)(ii), (i)(2)(ii), and (j) of
this AD accordingly.
Request To Revise Flight Cycle Limit
for Replacement Kit Skin Panels
Boeing requested that we revise
paragraph (l) of the proposed AD to
specify that skin panel replacements
using the kit identified in SASB 737–
53–1168, Revision 4, do not have the
lower flight cycle limit restriction that
the production skin panel replacements
have.
We agree with Boeing’s request
because the skin panel replacements
using the kit identified in SASB 737–
53–1168, Revision 4, is an improved
design compared to the production skin
panels, and therefore, do not need the
lower flight cycle limit restriction. We
have added paragraph (l)(3) to this AD,
which states, in part, that if the skin
panel is replaced with a kit skin panel
as specified in SASB 737–53–1168,
Revision 4, the 53,000 total flight cycle
limit does not apply.
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
24469
Request To Remove Flight-Cycle
Restriction for Certain Actions
Boeing requested that we revise
paragraphs (m)(2), (m)(3), and (n)(5) of
the proposed AD to remove the flight
cycle restriction for certain previously
accomplished actions using certain
service information. Boeing stated that
the only skin panel replacements
specified in previous revisions of SASB
737–53–1168 are those using the kit
panels, and that those panels do not
have the flight-cycle limit specified in
paragraphs (m)(2), (m)(3), and (n)(5) of
the proposed AD.
We agree with the commenter’s
request because the skin panel
replacements using the kit identified in
SASB 737–53–1168, Revision 4, are an
improved design compared to the
production skin panels, and therefore,
do not need the lower flight cycle limit
restriction. We have revised paragraphs
(m)(2), (m)(3), and (n)(5) of this AD
accordingly.
Request To Specify Terminating Action
Qantas Airways Limited (Qantas)
requested that we revise paragraphs (g)
and (l) of the proposed AD to specify
terminating action. Qantas pointed out
that replacing the skin panels with kit
panels instead of production panels, as
specified in SASB 737–53–1168,
terminates the repetitive inspections
identified in paragraphs (g), (i), and (j)
of the proposed AD. Additionally,
Qantas pointed out that replacement
with kit skin panels using any revision
of SASB 737–53–1168 before the
effective date of the AD should also
terminate the repetitive inspections
identified in paragraphs (g), (i), and (j)
of the proposed AD.
We agree with the commenter’s
request because the skin panel
replacements using the kit identified in
SASB 737–53–1168, Revision 4, are an
improved design compared to the
production skin panels and therefore,
should terminate the repetitive
inspections. We have revised
paragraphs (m)(2), (m)(3), and (n)(5) of
this AD accordingly.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing 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
E:\FR\FM\30MYR1.SGM
30MYR1
24470
Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Rules and Regulations
• 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.
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:
Costs of Compliance
Related Service Information Under 1
CFR Part 51
We reviewed SASB 737–53–1168,
Revision 4. The service information
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.
We estimate that this AD affects 168
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
describes procedures for doing
inspections of the fuselage skin, repairs,
and 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.
ESTIMATED COSTS
Action
Labor cost
Inspections ....................
Up to 1,791 work-hours × $85 per hour =
$152,235.
624 work-hours × $85 per hour = $53,040 ..........
Skin replacement ..........
We estimate the following costs to do
any necessary repairs that would be
Parts cost
Cost on U.S.
operators
Cost per product
$0
Up to $152,235 .............
Up to $25,575,480.
98,275
$151,315 .......................
$25,420,920.
required based on the results of the
inspections. We have no way of
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Time-limited repair ....................
Permanent repair ......................
24 work-hours × $85 per hour = $2,040 per repair ....................
Up to 43 work-hours × $85 per hour = $3,655 per repair ..........
1 We
Parts cost
Cost per product
(1 )
(1 )
$2,040 per repair.
Up to $3,655 per repair.
have received no definitive data that would enable us to provide the part cost estimates for the on-condition actions specified in this AD.
We estimate the following costs to do
any necessary post-repair inspections
that would be required. We have no way
of determining the number of aircraft
that might need these inspections:
POST-REPAIR INSPECTION COSTS
Action
Labor cost
Post-repair inspection ...............
Up to 7 work-hours × $85 per hour = $595 ...............................
sradovich on DSK3GMQ082PROD with RULES
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
VerDate Sep<11>2014
18:40 May 26, 2017
Jkt 241001
Parts cost
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,
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
Cost per product
$0
Up to $595.
(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,
E:\FR\FM\30MYR1.SGM
30MYR1
Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Rules and Regulations
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)
2009–21–01, Amendment 39–16038 (74
FR 52395, October 13, 2009), and
adding the following new AD:
■
2017–10–08 The Boeing Company:
Amendment 39–18882; Docket No.
FAA–2016–6667; Directorate Identifier
2015–NM–125–AD.
(a) Effective Date
This AD is effective July 5, 2017.
(b) Affected ADs
This AD replaces AD 2009–21–01,
Amendment 39–16038 (74 FR 52395, October
13, 2009) (‘‘AD 2009–21–01’’).
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–300 series airplanes,
certificated in any category, as identified in
Boeing Special Attention Service Bulletin
737–53–1168, Revision 4, dated June 3, 2015
(‘‘SASB 737–53–1168, Revision 4’’).
(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 53, Fuselage.
sradovich on DSK3GMQ082PROD with RULES
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that the aft fuselage skin is subject to
widespread fatigue damage (WFD), and
reports of aft fuselage cracking. We are
issuing this AD to detect and correct cracking
in the aft fuselage skin along the longitudinal
edges of the chem-milled pockets in the
bonded skin doubler, which could result in
possible rapid decompression and reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
VerDate Sep<11>2014
17:28 May 26, 2017
Jkt 241001
(g) Inspections, Related Investigative and
Corrective Actions
At the applicable times specified in tables
1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of
SASB 737–53–1168, Revision 4, except as
required by paragraphs (h)(1) and (h)(2) of
this AD: Do the applicable inspections to
detect cracks in the aft fuselage skin panels,
and do all applicable related investigative
and corrective actions, in accordance with
the Accomplishment Instructions of SASB
737–53–1168, Revision 4, except as required
by paragraphs (h)(3) and (h)(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 tables
1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of
SASB 737–53–1168, Revision 4.
Accomplishment of a repair in accordance
with ‘‘Part 4: Repair’’ of the Accomplishment
Instructions of SASB 737–53–1168, Revision
4, except as required by paragraph (h)(3) of
this AD, is terminating action for the
repetitive inspections required by this
paragraph at the repaired locations only.
(h) Exceptions to SASB 737–53–1168,
Revision 4
(1) Where SASB 737–53–1168, Revision 4,
specifies compliance times ‘‘after the
Revision 4 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 737–53–1168,
Revision 4, refers to airplanes in certain
configurations as of the ‘‘issue date of
Revision 4 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 737–53–1168, Revision 4,
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 (n) of this AD, except as required
by paragraph (h)(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 53,000 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
737–53–1168, Revision 4, except as provided
by paragraph (h)(1) and (h)(2) of this AD,
perform inspections and applicable
corrective actions using a method approved
in accordance with the procedures specified
in paragraph (n) of this AD.
(i) Actions for Airplanes With a TimeLimited Repair Installed
(1) For airplanes with a time-limited repair
installed, as specified in Boeing Service
Bulletin 737–53–1168, Revision 3, dated
November 28, 2006: At the applicable times
specified in table 3 of paragraph 1.E.,
‘‘Compliance,’’ of SASB 737–53–1168,
Revision 4, except as provided by paragraphs
(h)(1) and (h)(2) of this AD, do the actions
specified in paragraphs (i)(1)(i) and (i)(1)(ii)
of this AD.
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
24471
(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
737–53–1168, Revision 4, except as required
by paragraph (h)(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
737–53–1168, Revision 4.
(ii) Make the time-limited repair
permanent, and do all applicable related
investigative and corrective actions, in
accordance with Part 6 of the
Accomplishment Instructions of SASB 737–
53–1168, Revision 4, except as required by
paragraph (h)(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 (i)(1)(i) of this AD for the
permanently repaired area only.
(2) For airplanes with a time-limited repair
installed, as specified in SASB 737–53–1168,
Revision 4: At the applicable times specified
in table 4 of paragraph 1.E., ‘‘Compliance,’’
of SASB 737–53–1168, Revision 4, do the
actions specified in paragraphs (i)(2)(i) and
(i)(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
737–53–1168, Revision 4, except as required
by paragraph (h)(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 table
4 of paragraph 1.E., ‘‘Compliance,’’ of SASB
737–53–1168, Revision 4.
(ii) Make the time-limited repair
permanent, and do all applicable related
investigative and corrective actions, in
accordance with Part 6 of the
Accomplishment Instructions of SASB 737–
53–1168, Revision 4, except as required by
paragraph (h)(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 (i)(2)(i) of this AD for the
permanently repaired area only.
(j) Modification of Certain Permanent
Repairs
For airplanes with an existing time-limited
repair that was made permanent, as specified
in Boeing Service Bulletin 737–53–1168,
Revision 3, dated November 28, 2006: At the
applicable times specified in table 5 of
paragraph 1.E., ‘‘Compliance,’’ of SASB 737–
53–1168, Revision 4, except as provided by
paragraphs (h)(1) of this AD, modify the
existing permanent repair, and do all
applicable related investigative and
corrective actions, in accordance with Part 6
of the Accomplishment Instructions of SASB
737–53–1168, Revision 4, except as required
E:\FR\FM\30MYR1.SGM
30MYR1
24472
Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Rules and Regulations
by paragraph (h)(3) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
(k) Post-Repair Inspections
Table 6 of paragraph 1.E., ‘‘Compliance,’’
of SASB 737–53–1168, Revision 4, specifies
post-repair airworthiness limitation
inspections in compliance with 14 CFR
25.571(a)(3) at the repaired 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 AMOC.
sradovich on DSK3GMQ082PROD with RULES
(l) Skin Panel Replacement
At the later of the times specified in
paragraphs (l)(1), (1)(2), and (l)(3) of this AD:
Replace the applicable skin panels, and do
all applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of SASB 737–
53–1168, Revision 4. Do all applicable
related investigative and corrective actions
before further flight. Doing the skin panel
replacement required by this paragraph
terminates the inspection requirements of
paragraphs (g), (i), and (j) of this AD for that
skin panel only, provided the skin panel
replacement was done with a production
skin panel after 53,000 total flight cycles.
(1) Before 60,000 total flight cycles, but not
before 53,000 total flight cycles.
(2) Within 6,000 flight cycles after the
effective date of this AD, but not before
53,000 total flight cycles.
(3) If the skin panel is replaced with a
production skin panel, not before 53,000 total
flight cycles. If the skin panel is replaced
with a kit skin panel as specified in SASB
737–53–1168, Revision 4, the 53,000 total
flight cycle limit does not apply.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Service
Bulletin 737–53–1168, Revision 3, dated
November 28, 2006, except as required by
paragraph (h)(4) of this AD. Boeing Service
Bulletin 737–53–1168, Revision 3, dated
November 28, 2006, was incorporated by
reference in AD 2009–21–01.
(2) This paragraph provides credit for the
actions required by paragraph (l) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Service
Bulletin 737–53–1168, Revision 3, dated
November 28, 2006, except as required by
paragraph (h)(4) of this AD. Boeing Service
Bulletin 737–53–1168, Revision 3, dated
November 28, 2006, was incorporated by
reference in AD 2009–21–01.
(3) This paragraph provides credit for the
actions required by paragraph (l) of this AD,
if those actions were performed before
November 17, 2009 (the effective date of AD
2009–21–01), using any service information
specified in paragraphs (m)(3)(i), (m)(3)(ii),
and (m)(3)(iii) of this AD, provided the
replacement is made with a kit skin panel,
except as required by paragraph (h)(4) of this
VerDate Sep<11>2014
17:28 May 26, 2017
Jkt 241001
AD. The service information specified in
paragraphs (m)(3)(i), (m)(3)(ii), and (m)(3)(iii)
of this AD was incorporated by reference in
AD 2009–21–01.
(i) Part 3 of the Accomplishment
Instructions of Boeing Service Bulletin 737–
53–1168, dated March 16, 1995.
(ii) Part 3 of the Accomplishment
Instructions of Boeing Service Bulletin 737–
53–1168, Revision 1, dated August 17, 1995.
(iii) Part 3 of the Accomplishment
Instructions of Boeing Service Bulletin 737–
53–1168, Revision 2, dated November 27,
1996.
(n) 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 (o)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane and the
approval must specifically refer to this AD.
(4) AMOCs approved previously for repairs
required by AD 2009–21–01 are approved as
AMOCs for the corresponding provisions of
paragraph (g) of this AD.
(5) AMOCs approved previously for
modifications done as optional terminating
action for AD 2009–21–01 are approved as
AMOCs for the skin panel replacement
required by paragraph (l) of this AD.
(o) Related Information
(1) 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.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
(p) 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.
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
(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 737–53–1168, Revision 4, dated June
3, 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/ibrlocations.html.
Issued in Renton, Washington, on May 2,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10288 Filed 5–26–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0156; Directorate
Identifier 2017–CE–003–AD; Amendment
39–18877; AD 2017–10–03]
RIN 2120–AA64
Airworthiness Directives; ZLIN
AIRCRAFT a.s. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2003–11–
12 for ZLIN AIRCRAFT a.s. Model Z–
242L airplanes (type certificate
previously held by MORAVAN a.s.).
This AD results from mandatory
continuing airworthiness information
(MCAI) issued by an aviation authority
of another country to identify and
correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as a need to
incorporate new revisions into the
Limitations section, Chapter 9, of the
FAA-approved maintenance program
(e.g., maintenance manual) to impose
SUMMARY:
E:\FR\FM\30MYR1.SGM
30MYR1
Agencies
[Federal Register Volume 82, Number 102 (Tuesday, May 30, 2017)]
[Rules and Regulations]
[Pages 24468-24472]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10288]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6667; Directorate Identifier 2015-NM-125-AD;
Amendment 39-18882; AD 2017-10-08]
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) 2009-21-01 for
certain The Boeing Company Model 737-300 and 737-400 series airplanes.
AD 2009-21-01 required repetitive inspections to detect cracking of the
aft fuselage skin, and related investigative and corrective actions if
necessary. This new AD adds certain inspections, repairs, replacement,
related investigative and corrective actions if necessary; and removes
certain airplanes from the applicability. This AD was prompted by an
evaluation by the design approval holder (DAH) indicating that the aft
fuselage skin is subject to widespread fatigue damage (WFD), and by
reports of aft fuselage cracking. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective July 5, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 5,
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-
6667.
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-
6667; 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: 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 2009-21-01, Amendment 39-16038 (74 FR 52395,
October 13, 2009) (``AD 2009-21-01''). AD 2009-21-01 applied to certain
the Boeing Company Model 737-300 and 737-400 series airplanes. The NPRM
published in the Federal Register on May 13, 2016 (81 FR 29802). The
NPRM was prompted by an evaluation by the DAH indicating that the aft
fuselage skin is subject to WFD, and by reports of aft fuselage
cracking. The NPRM proposed to continue to require repetitive
inspections to detect cracking of the aft fuselage skin, and related
investigative and corrective actions if necessary. The NPRM also
proposed to add new aft 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. The NPRM also proposed to remove Model 737-400
series airplanes from the applicability. We are issuing this AD to
detect and correct cracking in the aft fuselage skin along the
longitudinal edges of the chem-milled pockets in the bonded skin
doubler, which could result in possible rapid decompression and reduced
structural integrity 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 the Precipitating Event Statement
Boeing requested that we revise the precipitating event statement
by including that there have been reports of aft fuselage cracking.
Boeing stated that this revision would be consistent with wording of
other related rulemaking.
We agree with Boeing's request because it provides additional
clarity to the precipitating event statement. We have revised the
SUMMARY and Discussion sections, and paragraph (e) of this AD
accordingly.
[[Page 24469]]
Request To Require Reinstalling Lap Joint Modification
Jet2.com Limited (Jet2) requested that we revise the NPRM to
require reinstalling the lap joint modification previously installed in
accordance with AD 2015-21-06, Amendment 39-18298 (80 FR 69839,
November 12, 2015) (``AD 2015-21-06''), which requires the S-14 lap
joint to be trimmed out prior to 50,000 total flight cycles. Jet2
stated that Boeing Special Attention Service Bulletin 737-53-1168,
Revision 4, dated June 3, 2015 (``SASB 737-53-1168, Revision 4'')
specifies reinstalling the lap joint modification.
We do not agree with the commenter's request. The modification
required in AD 2015-21-06 consists of trimming out the lap splice, such
that if this modification were installed, it would be impossible to
install a new skin without reinstalling the lap modification. If the
instructions in SASB 737-53-1168, Revision 4, to reinstall the lap
splice modification were accidently overlooked, it would become clear
to the installer that the reinstallation would be required. We have not
changed this AD in this regard.
Request To Address Certain Repairs
Boeing requested that we add a paragraph to the proposed AD to
address repairs that are installed on the airplane for reasons other
than chem-mill cracking. Boeing submitted suggested language and
pointed out that the additional language is similar to that in other
rulemaking.
We disagree with Boeing's request. Part 1 of the Accomplishment
Instructions of SASB 737-53-1168, Revision 4, does not make a
distinction regarding why an existing repair was installed. Therefore,
repairs installed for damage other than a chem-mill crack are already
addressed. We have not changed this AD in this regard.
Request To Revise Proposed Compliance Time
Boeing requested that we revise paragraph (h)(4) of the proposed AD
to do the actions at an initial compliance time obtained through the
alternative method of compliance (AMOC) process specified in paragraph
(n)(1) of the proposed AD. Boeing stated that the repetitive
inspections would still be done at the times specified in the service
information. Boeing also requested that we include in the paragraph
revision the terminating action of skin panel replacement at the time
approved through an AMOC. Boeing stated that its request would provide
a reset on the compliance times if the skin panel was replaced prior to
53,000 total airplane cycles. Boeing explained that its authorized
representative under the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) cannot approve extensions to the
compliance times.
We partially agree with Boeing's request. We agree that, for
airplanes with skin panels replaced prior to 53,000 total flight
cycles, in order to reset the inspection threshold on the replaced skin
panels, approval must come from the FAA. Under the provisions of
paragraph (n) of this AD, we may consider requests for a reset of the
compliance times if the skin panel was replaced prior to 53,000 total
airplane cycles if data are submitted to substantiate that such an
adjustment would provide an acceptable level of safety. We have not
changed this AD in this regard.
Request To Specify the Service Information Accomplishment Instructions
Part Numbers
Boeing requested that we add the specific part of the
accomplishment instructions in paragraphs (i)(1)(ii), (i)(2)(ii), and
(j) of the proposed AD. Boeing stated that paragraph (g) of the
proposed AD specifies the specific part number, and that this change
would make these paragraphs consistent with the wording in paragraph
(g) of the proposed AD.
We agree with Boeing's request. We agree that specifying the
specific part of the Accomplishment Instructions of SASB 737-53-1168,
Revision 4, will add clarity to the AD. We have revised paragraphs
(i)(1)(ii), (i)(2)(ii), and (j) of this AD accordingly.
Request To Revise Flight Cycle Limit for Replacement Kit Skin Panels
Boeing requested that we revise paragraph (l) of the proposed AD to
specify that skin panel replacements using the kit identified in SASB
737-53-1168, Revision 4, do not have the lower flight cycle limit
restriction that the production skin panel replacements have.
We agree with Boeing's request because the skin panel replacements
using the kit identified in SASB 737-53-1168, Revision 4, is an
improved design compared to the production skin panels, and therefore,
do not need the lower flight cycle limit restriction. We have added
paragraph (l)(3) to this AD, which states, in part, that if the skin
panel is replaced with a kit skin panel as specified in SASB 737-53-
1168, Revision 4, the 53,000 total flight cycle limit does not apply.
Request To Remove Flight-Cycle Restriction for Certain Actions
Boeing requested that we revise paragraphs (m)(2), (m)(3), and
(n)(5) of the proposed AD to remove the flight cycle restriction for
certain previously accomplished actions using certain service
information. Boeing stated that the only skin panel replacements
specified in previous revisions of SASB 737-53-1168 are those using the
kit panels, and that those panels do not have the flight-cycle limit
specified in paragraphs (m)(2), (m)(3), and (n)(5) of the proposed AD.
We agree with the commenter's request because the skin panel
replacements using the kit identified in SASB 737-53-1168, Revision 4,
are an improved design compared to the production skin panels, and
therefore, do not need the lower flight cycle limit restriction. We
have revised paragraphs (m)(2), (m)(3), and (n)(5) of this AD
accordingly.
Request To Specify Terminating Action
Qantas Airways Limited (Qantas) requested that we revise paragraphs
(g) and (l) of the proposed AD to specify terminating action. Qantas
pointed out that replacing the skin panels with kit panels instead of
production panels, as specified in SASB 737-53-1168, terminates the
repetitive inspections identified in paragraphs (g), (i), and (j) of
the proposed AD. Additionally, Qantas pointed out that replacement with
kit skin panels using any revision of SASB 737-53-1168 before the
effective date of the AD should also terminate the repetitive
inspections identified in paragraphs (g), (i), and (j) of the proposed
AD.
We agree with the commenter's request because the skin panel
replacements using the kit identified in SASB 737-53-1168, Revision 4,
are an improved design compared to the production skin panels and
therefore, should terminate the repetitive inspections. We have revised
paragraphs (m)(2), (m)(3), and (n)(5) of this AD accordingly.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing 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
[[Page 24470]]
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 737-53-1168, Revision 4. The service information
describes procedures for doing inspections of the fuselage skin,
repairs, and 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 168 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections.................. Up to 1,791 work- $0 Up to $152,235. Up to $25,575,480.
hours x $85 per
hour = $152,235.
Skin replacement............. 624 work-hours x $85 98,275 $151,315....... $25,420,920.
per hour = $53,040.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the inspections. We have no
way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Time-limited repair............. 24 work-hours x $85 per (\1\) $2,040 per repair.
hour = $2,040 per
repair.
Permanent repair................ Up to 43 work[dash]hours (\1\) Up to $3,655 per repair.
x $85 per hour = $3,655
per repair.
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that would enable us to provide the part cost estimates for the on-
condition actions specified in this AD.
We estimate the following costs to do any necessary post-repair
inspections that would be required. We have no way of determining the
number of aircraft that might need these inspections:
Post-Repair Inspection Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Post-repair inspection.......... Up to 7 work[dash]hours $0 Up to $595.
x $85 per hour = $595.
----------------------------------------------------------------------------------------------------------------
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,
[[Page 24471]]
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)
2009-21-01, Amendment 39-16038 (74 FR 52395, October 13, 2009), and
adding the following new AD:
2017-10-08 The Boeing Company: Amendment 39-18882; Docket No. FAA-
2016-6667; Directorate Identifier 2015-NM-125-AD.
(a) Effective Date
This AD is effective July 5, 2017.
(b) Affected ADs
This AD replaces AD 2009-21-01, Amendment 39-16038 (74 FR 52395,
October 13, 2009) (``AD 2009-21-01'').
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-300 series
airplanes, certificated in any category, as identified in Boeing
Special Attention Service Bulletin 737-53-1168, Revision 4, dated
June 3, 2015 (``SASB 737-53-1168, Revision 4'').
(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 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the aft fuselage skin is subject to
widespread fatigue damage (WFD), and reports of aft fuselage
cracking. We are issuing this AD to detect and correct cracking in
the aft fuselage skin along the longitudinal edges of the chem-
milled pockets in the bonded skin doubler, which could result in
possible rapid decompression and reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections, Related Investigative and Corrective Actions
At the applicable times specified in tables 1 and 2 of paragraph
1.E., ``Compliance,'' of SASB 737-53-1168, Revision 4, except as
required by paragraphs (h)(1) and (h)(2) of this AD: Do the
applicable inspections to detect cracks in the aft fuselage skin
panels, and do all applicable related investigative and corrective
actions, in accordance with the Accomplishment Instructions of SASB
737-53-1168, Revision 4, except as required by paragraphs (h)(3) and
(h)(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
tables 1 and 2 of paragraph 1.E., ``Compliance,'' of SASB 737-53-
1168, Revision 4. Accomplishment of a repair in accordance with
``Part 4: Repair'' of the Accomplishment Instructions of SASB 737-
53-1168, Revision 4, except as required by paragraph (h)(3) of this
AD, is terminating action for the repetitive inspections required by
this paragraph at the repaired locations only.
(h) Exceptions to SASB 737-53-1168, Revision 4
(1) Where SASB 737-53-1168, Revision 4, specifies compliance
times ``after the Revision 4 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 737-53-1168, Revision 4, refers to airplanes in certain
configurations as of the ``issue date of Revision 4 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 737-53-1168, Revision 4, 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
(n) of this AD, except as required by paragraph (h)(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 53,000 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 737-53-1168, Revision 4, except as provided by paragraph (h)(1)
and (h)(2) of this AD, perform inspections and applicable corrective
actions using a method approved in accordance with the procedures
specified in paragraph (n) of this AD.
(i) Actions for Airplanes With a Time-Limited Repair Installed
(1) For airplanes with a time-limited repair installed, as
specified in Boeing Service Bulletin 737-53-1168, Revision 3, dated
November 28, 2006: At the applicable times specified in table 3 of
paragraph 1.E., ``Compliance,'' of SASB 737-53-1168, Revision 4,
except as provided by paragraphs (h)(1) and (h)(2) of this AD, do
the actions specified in paragraphs (i)(1)(i) and (i)(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 737-53-1168,
Revision 4, except as required by paragraph (h)(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 737-53-1168, Revision 4.
(ii) Make the time-limited repair permanent, and do all
applicable related investigative and corrective actions, in
accordance with Part 6 of the Accomplishment Instructions of SASB
737-53-1168, Revision 4, except as required by paragraph (h)(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 (i)(1)(i) of this AD for the permanently repaired area
only.
(2) For airplanes with a time-limited repair installed, as
specified in SASB 737-53-1168, Revision 4: At the applicable times
specified in table 4 of paragraph 1.E., ``Compliance,'' of SASB 737-
53-1168, Revision 4, do the actions specified in paragraphs
(i)(2)(i) and (i)(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 737-53-1168,
Revision 4, except as required by paragraph (h)(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 table 4 of paragraph 1.E.,
``Compliance,'' of SASB 737-53-1168, Revision 4.
(ii) Make the time-limited repair permanent, and do all
applicable related investigative and corrective actions, in
accordance with Part 6 of the Accomplishment Instructions of SASB
737-53-1168, Revision 4, except as required by paragraph (h)(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 (i)(2)(i) of this AD for the permanently repaired area
only.
(j) Modification of Certain Permanent Repairs
For airplanes with an existing time-limited repair that was made
permanent, as specified in Boeing Service Bulletin 737-53-1168,
Revision 3, dated November 28, 2006: At the applicable times
specified in table 5 of paragraph 1.E., ``Compliance,'' of SASB 737-
53-1168, Revision 4, except as provided by paragraphs (h)(1) of this
AD, modify the existing permanent repair, and do all applicable
related investigative and corrective actions, in accordance with
Part 6 of the Accomplishment Instructions of SASB 737-53-1168,
Revision 4, except as required
[[Page 24472]]
by paragraph (h)(3) of this AD. Do all applicable related
investigative and corrective actions before further flight.
(k) Post-Repair Inspections
Table 6 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1168,
Revision 4, specifies post-repair airworthiness limitation
inspections in compliance with 14 CFR 25.571(a)(3) at the repaired
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 AMOC.
(l) Skin Panel Replacement
At the later of the times specified in paragraphs (l)(1),
(1)(2), and (l)(3) of this AD: Replace the applicable skin panels,
and do all applicable related investigative and corrective actions,
in accordance with the Accomplishment Instructions of SASB 737-53-
1168, Revision 4. Do all applicable related investigative and
corrective actions before further flight. Doing the skin panel
replacement required by this paragraph terminates the inspection
requirements of paragraphs (g), (i), and (j) of this AD for that
skin panel only, provided the skin panel replacement was done with a
production skin panel after 53,000 total flight cycles.
(1) Before 60,000 total flight cycles, but not before 53,000
total flight cycles.
(2) Within 6,000 flight cycles after the effective date of this
AD, but not before 53,000 total flight cycles.
(3) If the skin panel is replaced with a production skin panel,
not before 53,000 total flight cycles. If the skin panel is replaced
with a kit skin panel as specified in SASB 737-53-1168, Revision 4,
the 53,000 total flight cycle limit does not apply.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 737-53-1168,
Revision 3, dated November 28, 2006, except as required by paragraph
(h)(4) of this AD. Boeing Service Bulletin 737-53-1168, Revision 3,
dated November 28, 2006, was incorporated by reference in AD 2009-
21-01.
(2) This paragraph provides credit for the actions required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 737-53-1168,
Revision 3, dated November 28, 2006, except as required by paragraph
(h)(4) of this AD. Boeing Service Bulletin 737-53-1168, Revision 3,
dated November 28, 2006, was incorporated by reference in AD 2009-
21-01.
(3) This paragraph provides credit for the actions required by
paragraph (l) of this AD, if those actions were performed before
November 17, 2009 (the effective date of AD 2009-21-01), using any
service information specified in paragraphs (m)(3)(i), (m)(3)(ii),
and (m)(3)(iii) of this AD, provided the replacement is made with a
kit skin panel, except as required by paragraph (h)(4) of this AD.
The service information specified in paragraphs (m)(3)(i),
(m)(3)(ii), and (m)(3)(iii) of this AD was incorporated by reference
in AD 2009-21-01.
(i) Part 3 of the Accomplishment Instructions of Boeing Service
Bulletin 737-53-1168, dated March 16, 1995.
(ii) Part 3 of the Accomplishment Instructions of Boeing Service
Bulletin 737-53-1168, Revision 1, dated August 17, 1995.
(iii) Part 3 of the Accomplishment Instructions of Boeing
Service Bulletin 737-53-1168, Revision 2, dated November 27, 1996.
(n) 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 (o)(1) of this AD.
Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane and the approval must
specifically refer to this AD.
(4) AMOCs approved previously for repairs required by AD 2009-
21-01 are approved as AMOCs for the corresponding provisions of
paragraph (g) of this AD.
(5) AMOCs approved previously for modifications done as optional
terminating action for AD 2009-21-01 are approved as AMOCs for the
skin panel replacement required by paragraph (l) of this AD.
(o) Related Information
(1) 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.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
(p) 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 737-53-1168,
Revision 4, dated June 3, 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 May 2, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10288 Filed 5-26-17; 8:45 am]
BILLING CODE 4910-13-P