Airworthiness Directives; The Boeing Company Airplanes, 74599-74603 [2014-29190]
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Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of
cracking at the splice plate of the frame (FR)
47 butt joint crossing area found during fullscale fatigue testing. We are issuing this AD
to detect and correct fatigue cracking of the
splice plate of the FR47 butt joint crossing
area, which could result in reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Repetitive Inspections
At the applicable time specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD:
Do a special detailed inspection (rototest) for
cracking of both sides of the splice plate of
the FR47 butt joint crossing area, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1260, dated December 19, 2012. Repeat
the inspection thereafter at intervals not to
exceed 14,800 flight cycles or 29,600 flight
hours, whichever occurs first.
(1) For airplanes that, as of the effective
date of this AD, have accumulated 44,000 or
more total flight cycles or 88,000 or more
total flight hours since first flight of the
airplane: Do the inspection within 1,500
flight cycles or 3,000 flight hours after the
effective date of this AD, whichever occurs
first.
(2) For airplanes that, as of the effective
date of this AD, have accumulated 27,700 or
more total flight cycles or 55,400 or more
total flight hours, but fewer than 44,000 total
flight cycles or 88,000 total flight hours since
first flight of the airplane: Do the inspection
within 3,000 flight cycles or 6,000 flight
hours after the effective date of this AD,
without exceeding 45,500 total flight cycles
or 91,000 total flight hours since first flight
of the airplane, whichever occurs first.
(3) For airplanes that, as of the effective
date of this AD, have accumulated fewer than
27,700 total flight cycles and less than 55,400
total flight hours since first flight of the
airplane: Do the inspection before the
accumulation of 30,700 total flight cycles or
61,400 total flight hours since first flight of
the airplane, whichever occurs first.
(h) Corrective Action
If any crack is found during any inspection
required by this AD: Before further flight,
repair using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(i) Optional Modification
Accomplishing the modification of the
splice plate of the FR47 butt joint in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
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53–1271, dated December 18, 2012,
constitutes terminating action for the
repetitive inspections required by paragraph
(g) of this AD.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–227–1405; fax: 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(k) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0203, dated
September 6, 2013, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.
gov/#!documentDetail;D=FAA-2014-04530002.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–53–1260,
dated December 19, 2012.
(ii) Airbus Service Bulletin A320–53–1271,
dated December 18, 2012.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
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74599
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
December 3, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–29174 Filed 12–15–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0257; Directorate
Identifier 2014–NM–012–AD; Amendment
39–18051; AD 2014–25–09]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–100,
–200, –200C, –300, –400, and –500
series airplanes. This AD was prompted
by reports of fatigue cracking in the skin
assembly and bear strap of the aft lower
corner of the forward airstair stowage
doorway. This AD requires repetitive
inspections for cracking of the skin
assembly and bear strap of the forward
airstair stowage doorway; post-repair
and post-modification inspections for
certain airplanes; and related
investigative and corrective actions, if
necessary. This AD also provides
optional terminating actions for certain
inspections. We are issuing this AD to
detect and correct fatigue cracking,
which could result in rapid loss of cabin
pressure.
DATES: This AD is effective January 20,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 20, 2015.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
SUMMARY:
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Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations
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.
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–2014–
0257; 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:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: (425) 917–6450;
fax: (425) 917–6590; email: alan.pohl@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. The
NPRM published in the Federal
Register on May 1, 2014 (79 FR 24628).
The NPRM was prompted by reports of
fatigue cracking in certain areas. The
NPRM proposed to require repetitive
inspections for cracking of the skin
assembly and bear strap of the forward
airstair stowage doorway; post-repair
and post-modification inspections for
certain airplanes; and related
investigative and corrective actions, if
necessary. The NPRM also proposed to
provide optional terminating actions for
certain inspections. We are issuing this
AD to detect and correct fatigue
cracking, which could result in rapid
loss of cabin pressure.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 24628,
May 1, 2014) and the FAA’s response to
each comment.
Effect of Winglets on AD
Aviation Partners Boeing and UPS
stated that the installation of winglets
per Supplemental Type Certificate
(STC) ST01219SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257
cb30045557a/$FILE/ST01219SE.pdf)
does not affect the accomplishment of
the manufacturer’s service instructions.
We agree with the commenters’
statement. We have redesignated
paragraph (c) of the NPRM (79 FR
24628, May 1, 2014) as (c)(1) in this AD
and added new paragraph (c)(2) to this
AD to state that the installation of
winglets as specified in STC ST01219SE
(https://rgl.faa.gov/Regulatory_and_
Guidance_Library/rgstc.nsf/0/ebd1c
ec7b301293e86257cb30045557a/$FILE/
ST01219SE.pdf) does not affect
accomplishment of the requirements of
this AD, and 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 section 39.17 of the
Federal Aviation Regulations (14 CFR
39.17).
Request To Revise Paragraph (m) of the
NPRM (79 FR 24628, May 1, 2014)
Southwest Airlines (SWA) stated that
the NPRM (79 FR 24628, May 1, 2014),
does not address terminating the initial
inspection if a repair was previously
installed using Boeing Service Bulletin
737–53–1058, Revision 4, dated January
9, 2014. SWA requested that we revise
the text of paragraph (m)(3) of the
NPRM, to state that repairs or
modifications using Boeing Service
Bulletin 737–53–1058, Revision 4, dated
January 9, 2014, terminates both the
initial and repetitive inspections
required by paragraph (j) of this AD.
SWA also requested that repairs
previously approved by a Boeing
authorized representative via an FAA
8100–9 form are terminating action to
both the initial and repetitive inspection
requirements required by paragraph (j)
of the NPRM.
We agree with the request because it
was not intended that a separate initial
inspection would be performed on
airplanes that have the repair previously
installed. We have deleted the word
‘‘repetitive’’ from paragraphs (m)(1)
through (m)(3) of this AD to clarify that
accomplishing the actions in those
paragraphs terminates certain initial and
repetitive inspections. We have also
added paragraph (m)(4) to this final
rule, which specifies that the
accomplishment of a repair of the aft
lower corner of the forward airstair
stowage doorway that was previously
approved using FAA Form 8100–9,
terminates the inspections required by
paragraph (j) 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:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
24628, May 1, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 24628,
May 1, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 132
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Labor cost
Parts cost
Cost per product
Inspection ......
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Action
5 work-hours × $85 per hour = $425 per inspection
cycle.
None ............
$425 per inspection cycle
We have received no definitive data
that would enable us to provide cost
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estimates for any on-condition actions
specified in this AD.
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Cost on U.S. operators
$56,100 per inspection
cycle.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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:
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■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
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2014–25–09 The Boeing Company:
Amendment 39–18051; Docket No.
FAA–2014–0257; Directorate Identifier
2014–NM–012–AD.
(a) Effective Date
This AD is effective January 20, 2015.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category, as identified in
Boeing Service Bulletin 737–53–1058,
Revision 4, dated January 9, 2014.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://rgl.faa.
gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb300
45557a/$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.
74601
times specified in Table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
737–53–1058, Revision 4, dated January 9,
2014, until the applicable terminating action
specified in paragraph (m) of this AD is done.
(1) Boeing Service Bulletin 737–53–1058,
dated April 4, 1980.
(2) Boeing Service Bulletin 737–53–1058,
Revision 1, dated March 5, 1987.
(3) Boeing Service Bulletin 737–53–1058,
Revision 2, dated December 7, 1989.
(4) Boeing Service Bulletin 737–53–1058,
Revision 3, dated March 11, 1993.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(h) Inspections and Corrective Actions for
Group 1 and Group 2 Airplanes That Have
a Certain Repair Installed
For Group 1 and Group 2 airplanes
identified in Boeing Service Bulletin 737–53–
1058, Revision 4, dated January 9, 2014, on
which a repair has been installed as specified
in Boeing Service Bulletin 737–53–1058,
dated April 4, 1980: Within the applicable
times specified in Table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
737–53–1058, Revision 4, dated January 9,
2014, except as required by paragraph (o)(1)
of this AD, do a high frequency eddy current
inspection for cracking of the bear strap of
the forward airstair stowage doorway, and do
low frequency eddy current and detailed
inspections for cracking of the skin assembly
and bear strap of the forward airstair stowage
doorway; and do all applicable related
investigative and corrective actions; in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 737–
53–1058, Revision 4, dated January 9, 2014,
except as required by paragraph (o)(2) of this
AD. Do all applicable related investigative
and corrective actions before further flight.
Repeat the inspections at the applicable
times specified in Table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
737–53–1058, Revision 4, dated January 9,
2014, until the applicable terminating action
specified in paragraph (m) of this AD is done.
(g) Inspections and Corrective Actions for
Group 1 and Group 2 Airplanes That Do Not
Have a Certain Repair or Preventative
Modification Installed
For Group 1 and Group 2 airplanes
identified in Boeing Service Bulletin 737–53–
1058, Revision 4, dated January 9, 2014, on
which no repair or preventative modification
has been done as specified in any of the
service information identified in paragraphs
(g)(1) through (g)(4) of this AD: At the
applicable times specified in Table 1 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 737–53–1058, Revision 4,
dated January 9, 2014, except as required by
paragraph (o)(1) of this AD, do high
frequency eddy current and detailed
inspections for cracking of the skin assembly
and bear strap of the forward airstair stowage
doorway, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 737–
53–1058, Revision 4, dated January 9, 2014,
except as required by paragraph (o)(2) of this
AD. Do all applicable related investigative
and corrective actions before further flight.
Repeat the inspections at the applicable
(i) Inspections and Corrective Actions for
Group 1 and Group 2 Airplanes That Have
a Certain Preventative Modification
Installed
For Group 1 and Group 2 airplanes
identified in Boeing Service Bulletin 737–53–
1058, Revision 4, dated January 9, 2014, on
which a preventative modification has been
installed as specified in any of the service
information identified in paragraphs (i)(1)
through (i)(4) of this AD: Within the
applicable times specified in Table 1 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 737–53–1058, Revision 4,
dated January 9, 2014, except as required by
paragraph (o)(1) of this AD, do a high
frequency eddy current inspection for
cracking of the bear strap of the forward
airstair stowage doorway, a low frequency
eddy current inspection for cracking of the
skin assembly and bear strap of the forward
airstair stowage doorway, and detailed
inspections for cracking of the skin assembly
and bear strap of the forward airstair stowage
doorway; and do all related investigative and
applicable corrective actions; in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 737–53–1058,
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
fatigue cracking in the skin assembly and
bear strap of the aft lower corner of the
forward airstair stowage doorway. We are
issuing this AD to detect and correct fatigue
cracking, which could result in rapid loss of
cabin pressure.
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Revision 4, dated January 9, 2014, except as
required by paragraph (o)(2) of this AD. Do
all applicable related investigative and
corrective actions before further flight.
Repeat the inspections at the applicable
times specified in Table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
737–53–1058, Revision 4, dated January 9,
2014, until the applicable terminating action
specified in paragraph (m) of this AD is done.
(1) Boeing Service Bulletin 737–53–1058,
dated April 4, 1980.
(2) Boeing Service Bulletin 737–53–1058,
Revision 1, dated March 5, 1987.
(3) Boeing Service Bulletin 737–53–1058,
Revision 2, dated December 7, 1989.
(4) Boeing Service Bulletin 737–53–1058,
Revision 3, dated March 11, 1993.
(j) Inspections and Corrective Actions for
Group 3 Through Group 5 Airplanes
For Group 3 through Group 5 airplanes
identified in Boeing Service Bulletin 737–53–
1058, Revision 4, dated January 9, 2014: At
the applicable times specified in Table 2 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 737–53–1058, Revision 4,
dated January 9, 2014, except as required by
paragraph (o)(1) of this AD, do a high
frequency eddy current inspection for
cracking of the bear strap of the forward
airstair stowage doorway, a low frequency
eddy current inspection for cracking of the
skin assembly and bear strap of the forward
airstair stowage doorway, and detailed
inspections for cracking of the skin assembly
and bear strap of the forward airstair stowage
doorway; and do all related investigative and
applicable corrective actions; in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 737–53–1058,
Revision 4, dated January 9, 2014, except as
required by paragraph (o)(2) of this AD. Do
all applicable related investigative and
corrective actions before further flight.
Repeat the inspections at the applicable
times specified in Table 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
737–53–1058, Revision 4, dated January 9,
2014, until the applicable terminating action
specified in paragraph (m) of this AD is done.
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(k) Inspections and Corrective Actions for
Group 6 Airplanes
For Group 6 airplanes identified in Boeing
Service Bulletin 737–53–1058, Revision 4,
dated January 9, 2014: Within 120 days after
the effective date of this AD, inspect and
repair any cracking using a method approved
in accordance with the procedures specified
in paragraph (q) of this AD.
(l) Post-Repair and Post-Modification
Inspections for Group 1 and Group 2
Airplanes
For Group 1 and Group 2 airplanes on
which any repair has been done as specified
in any of the service information identified
in paragraphs (l)(1) through (l)(3) of this AD,
or on which any repair or modification has
been done as specified in the service
information identified in paragraph (l)(4) of
this AD: At the applicable times specified in
Table 3 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Service Bulletin 737–53–1058,
Revision 4, dated January 9, 2014, except as
required by paragraph (o)(1) of this AD, do
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a high frequency eddy current inspection for
cracking in the bear strap and skin assembly
and a general visual inspection for cracking
in the frame of the forward airstair stowage
doorway; or do low frequency eddy current
inspections for cracking of the skin assembly
and bear strap of the forward airstair stowage
doorway; in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 737–53–1058, Revision 4,
dated January 9, 2014. Options provided in
Boeing Service Bulletin 737–53–1058,
Revision 4, dated January 9, 2014, for
accomplishing the inspections are acceptable
for compliance with the corresponding
requirements of this paragraph provided that
the inspections are done at the applicable
times specified in paragraph 1.E.,
‘‘Compliance,’’ of the Boeing Service Bulletin
737–53–1058, Revision 4, dated January 9,
2014. If any cracking is found, before further
flight, repair the cracking using a method
approved in accordance with the procedures
specified in paragraph (q) of this AD. Repeat
the inspections at the applicable times
specified in Table 3 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
737–53–1058, Revision 4, dated January 9,
2014.
(1) Boeing Service Bulletin 737–53–1058,
Revision 1, dated March 5, 1987.
(2) Boeing Service Bulletin 737–53–1058,
Revision 2, dated December 7, 1989.
(3) Boeing Service Bulletin 737–53–1058,
Revision 3, dated March 11, 1993.
(4) Boeing Service Bulletin 737–53–1058,
Revision 4, dated January 9, 2014.
(m) Optional Terminating Actions
(1) For Group 1 and Group 2 airplanes
identified in Boeing Service Bulletin 737–53–
1058, Revision 4, dated January 9, 2014:
Accomplishment of a repair for cracking of
the skin assembly and bear strap of the
forward airstair stowage doorway before the
effective date of this AD, using any service
information specified in paragraphs (m)(1)(i)
through (m)(1)(iv) of this AD, terminates the
inspections required by paragraphs (g), (h),
and (i) of this AD.
(i) Boeing Service Bulletin 737–53–1058,
Revision 1, dated March 5, 1987.
(ii) Boeing Service Bulletin 737–53–1058,
Revision 2, dated December 7, 1989.
(iii) Boeing Service Bulletin 737–53–1058,
Revision 3, dated March 11, 1993.
(iv) Boeing Service Bulletin 737–53–1058,
Revision 4, dated January 9, 2014.
(2) For Group 1 and Group 2 airplanes
identified in Boeing Service Bulletin 737–53–
1058, Revision 4, dated January 9, 2014:
Accomplishment of a preventative
modification for cracking of the skin
assembly and bear strap of the forward
airstair stowage doorway before the effective
date of this AD, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 737–53–1058, Revision 4,
dated January 9, 2014, terminates the
inspections required by paragraphs (g), (h),
and (i) of this AD.
(3) For Group 3 through Group 5 airplanes
identified in Boeing Service Bulletin 737–53–
1058, Revision 4, dated January 9, 2014:
Repairing or modifying the forward airstair
stowage doorway, in accordance with the
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
Accomplishment Instructions of Boeing
Service Bulletin 737–53–1058, Revision 4,
dated January 9, 2014, terminates the
inspections required by paragraph (j) of this
AD.
(4) Accomplishment, prior to the effective
date of this AD, of a repair of the aft lower
corner of the forward airstair stowage
doorway that was approved by Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) using FAA
Form 8100–9, terminates the inspections
required by paragraph (j) of this AD.
(n) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (g), (h), and
(i) of this AD, if those actions were performed
before the effective date of this AD using any
service information specified in paragraphs
(n)(i) through (n)(iii) of this AD.
(i) Boeing Service Bulletin 737–53–1058,
Revision 1, dated March 5, 1987.
(ii) Boeing Service Bulletin 737–53–1058,
Revision 2, dated December 7, 1989.
(iii) Boeing Service Bulletin 737–53–1058,
Revision 3, dated March 11, 1993.
(o) Exceptions to the Service Information
(1) Where Boeing Service Bulletin 737–53–
1058, Revision 4, dated January 9, 2014,
specifies a compliance time ‘‘after the
Revision 4 date of this service bulletin,’’ this
AD requires compliance within the specified
compliance time ‘‘after the effective date of
this AD.’’
(2) Where Boeing Service Bulletin 737–53–
1058, Revision 4, dated January 9, 2014,
specifies to contact Boeing for repair
instructions: Before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (q) of
this AD.
(p) Post-Repair and Post-Modification
Inspections for Group 3 Through Group 5
Airplanes Not Required
The post-repair and post-modification
inspections specified in Table 4 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 737–53–1058, Revision 4, dated
January 9, 2014, are not required by this AD.
Note 1 to paragraph (p) of this AD: The
post-repair and post-modification inspections
specified in Table 4 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
737–53–1058, Revision 4, dated January 9,
2014, may be used in support of compliance
with section 121.1109(c)(2) or 129.109(b)(2)
of the Federal Aviation Regulations (14 CFR
121.1109(c)(2) or 14 CFR 129.109(b)(2)).
(q) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (r)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
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(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
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. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(r) Related Information
(1) For more information about this AD,
contact Nenita Odesa, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, CA 90712–
4137; phone: (562) 627–5234; fax: (562) 627–
5210; email: nenita.odesa@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (s)(3) and (s)(4) of this AD.
(s) Material Incorporated by Reference
tkelley on DSK3SPTVN1PROD with RULES
(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 Service Bulletin 737–53–1058,
Revision 4, dated January 9, 2014.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(4) You may view this service information
at 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
December 5, 2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–29190 Filed 12–15–14; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
16:25 Dec 15, 2014
Jkt 235001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0566; Directorate
Identifier 2014–NM–041–AD; Amendment
39–18050; AD 2014–25–08]
RIN 2120–AA64
Airworthiness Directives; Dassault
Aviation Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Dassault Aviation Model FALCON 2000
and FALCON 2000EX airplanes. This
AD was prompted by a design review,
which revealed that the forward
servicing compartment (FSC) is
configured with tie-down points. This
AD requires inspecting the FSC for
installed tie-down points, and removing
those tie-down points. We are issuing
this AD to detect and correct installed
tie-down points, which could lead to
inadvertent use of the FSC as a cargo
compartment, which could result in
damage to the structure of the airplane
or potential risk of fire.
DATES: This AD becomes effective
January 20, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 20, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://www.
regulations.gov/#!docketDetail;D=FAA2014-0566; or in person at the 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.
For service information identified in
this AD, contact Dassault Falcon Jet,
P.O. Box 2000, South Hackensack, NJ
07606; telephone 201–440–6700;
Internet https://www.dassaultfalcon.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.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1137;
fax 425- 227–1149.
SUMMARY:
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74603
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Dassault Aviation
Model FALCON 2000 and FALCON
2000EX airplanes. The NPRM published
in the Federal Register on August 14,
2014 (79 FR 47592).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2014–0027R1,
dated February 5, 2014 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Dassault Aviation Model
FALCON 2000 and FALCON 2000EX
airplanes. The MCAI states:
The Forward Servicing Compartment (FSC)
of the Falcon 2000 is an unpressurized
service compartment located between
fuselage frames 26 and 33. This compartment
is accessible from a lockable external door
located in the lower aft fuselage.
A design review has brought to light that
the compartment is configured with tie-down
points, which were used by operators to fix
loads (e.g. ski or golf bags) in that
compartment. However, the FSC has not been
designed and consequently demonstrated as
being compliant with cargo compartment
airworthiness requirements.
This condition, if not corrected, could lead
to inadvertent use of the FSC as [a] cargo
compartment, which could result in damage
to the structure of the aeroplane or potential
risk of fire.
To address this potential unsafe condition,
Dassault Aviation issued Service Bulletin
(SB) F2000–407 and SB F2000EX–289, as
applicable, which provide instructions for
removal of the tie-down points.
For the reasons described above, this
[EASA] AD requires removal of the tie-down
points from the FSC.
Note: Operators are also reminded about
the intended function of the FSC.
This [EASA] AD is revised to clarify the
AD Applicability and to correct the [type
certificate data sheet] TCDS Number.
Required actions include inspecting
for installed tie-down points. You may
examine the MCAI in the AD docket on
the Internet at https://www.regulations.
gov/#!documentDetail;D=FAA-20140566-0002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
FR 47592, August 14, 2014) or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
E:\FR\FM\16DER1.SGM
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]]>Agencies
[Federal Register Volume 79, Number 241 (Tuesday, December 16, 2014)]
[Rules and Regulations]
[Pages 74599-74603]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-29190]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0257; Directorate Identifier 2014-NM-012-AD;
Amendment 39-18051; AD 2014-25-09]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. This AD was prompted by reports of fatigue cracking
in the skin assembly and bear strap of the aft lower corner of the
forward airstair stowage doorway. This AD requires repetitive
inspections for cracking of the skin assembly and bear strap of the
forward airstair stowage doorway; post-repair and post-modification
inspections for certain airplanes; and related investigative and
corrective actions, if necessary. This AD also provides optional
terminating actions for certain inspections. We are issuing this AD to
detect and correct fatigue cracking, which could result in rapid loss
of cabin pressure.
DATES: This AD is effective January 20, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 20,
2015.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://
[[Page 74600]]
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.
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-2014-
0257; 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: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-6450;
fax: (425) 917-6590; email: alan.pohl@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on May 1, 2014 (79 FR 24628).
The NPRM was prompted by reports of fatigue cracking in certain areas.
The NPRM proposed to require repetitive inspections for cracking of the
skin assembly and bear strap of the forward airstair stowage doorway;
post-repair and post-modification inspections for certain airplanes;
and related investigative and corrective actions, if necessary. The
NPRM also proposed to provide optional terminating actions for certain
inspections. We are issuing this AD to detect and correct fatigue
cracking, which could result in rapid loss of cabin pressure.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 24628, May 1, 2014) and the FAA's response to each comment.
Effect of Winglets on AD
Aviation Partners Boeing and UPS stated that the installation of
winglets per Supplemental Type Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect
the accomplishment of the manufacturer's service instructions.
We agree with the commenters' statement. We have redesignated
paragraph (c) of the NPRM (79 FR 24628, May 1, 2014) as (c)(1) in this
AD and added new paragraph (c)(2) to this AD to state that the
installation of winglets as specified in STC ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect
accomplishment of the requirements of this AD, and 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 section 39.17 of the Federal Aviation
Regulations (14 CFR 39.17).
Request To Revise Paragraph (m) of the NPRM (79 FR 24628, May 1, 2014)
Southwest Airlines (SWA) stated that the NPRM (79 FR 24628, May 1,
2014), does not address terminating the initial inspection if a repair
was previously installed using Boeing Service Bulletin 737-53-1058,
Revision 4, dated January 9, 2014. SWA requested that we revise the
text of paragraph (m)(3) of the NPRM, to state that repairs or
modifications using Boeing Service Bulletin 737-53-1058, Revision 4,
dated January 9, 2014, terminates both the initial and repetitive
inspections required by paragraph (j) of this AD. SWA also requested
that repairs previously approved by a Boeing authorized representative
via an FAA 8100-9 form are terminating action to both the initial and
repetitive inspection requirements required by paragraph (j) of the
NPRM.
We agree with the request because it was not intended that a
separate initial inspection would be performed on airplanes that have
the repair previously installed. We have deleted the word
``repetitive'' from paragraphs (m)(1) through (m)(3) of this AD to
clarify that accomplishing the actions in those paragraphs terminates
certain initial and repetitive inspections. We have also added
paragraph (m)(4) to this final rule, which specifies that the
accomplishment of a repair of the aft lower corner of the forward
airstair stowage doorway that was previously approved using FAA Form
8100-9, terminates the inspections required by paragraph (j) 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:
[Agr]re consistent with the intent that was proposed in
the NPRM (79 FR 24628, May 1, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 24628, May 1, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 132 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection........... 5 work-hours x $85 per None................ $425 per inspection $56,100 per
hour = $425 per cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for any on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue
[[Page 74601]]
rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2014-25-09 The Boeing Company: Amendment 39-18051; Docket No. FAA-
2014-0257; Directorate Identifier 2014-NM-012-AD.
(a) Effective Date
This AD is effective January 20, 2015.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category, as identified in Boeing Service Bulletin 737-53-1058,
Revision 4, dated January 9, 2014.
(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 reports of fatigue cracking in the skin
assembly and bear strap of the aft lower corner of the forward
airstair stowage doorway. We are issuing this AD to detect and
correct fatigue cracking, which could result in rapid loss of cabin
pressure.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections and Corrective Actions for Group 1 and Group 2
Airplanes That Do Not Have a Certain Repair or Preventative
Modification Installed
For Group 1 and Group 2 airplanes identified in Boeing Service
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, on which no
repair or preventative modification has been done as specified in
any of the service information identified in paragraphs (g)(1)
through (g)(4) of this AD: At the applicable times specified in
Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, except as
required by paragraph (o)(1) of this AD, do high frequency eddy
current and detailed inspections for cracking of the skin assembly
and bear strap of the forward airstair stowage doorway, and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, except as
required by paragraph (o)(2) of this AD. Do all applicable related
investigative and corrective actions before further flight. Repeat
the inspections at the applicable times specified in Table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-53-
1058, Revision 4, dated January 9, 2014, until the applicable
terminating action specified in paragraph (m) of this AD is done.
(1) Boeing Service Bulletin 737-53-1058, dated April 4, 1980.
(2) Boeing Service Bulletin 737-53-1058, Revision 1, dated March
5, 1987.
(3) Boeing Service Bulletin 737-53-1058, Revision 2, dated
December 7, 1989.
(4) Boeing Service Bulletin 737-53-1058, Revision 3, dated March
11, 1993.
(h) Inspections and Corrective Actions for Group 1 and Group 2
Airplanes That Have a Certain Repair Installed
For Group 1 and Group 2 airplanes identified in Boeing Service
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, on which a
repair has been installed as specified in Boeing Service Bulletin
737-53-1058, dated April 4, 1980: Within the applicable times
specified in Table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014,
except as required by paragraph (o)(1) of this AD, do a high
frequency eddy current inspection for cracking of the bear strap of
the forward airstair stowage doorway, and do low frequency eddy
current and detailed inspections for cracking of the skin assembly
and bear strap of the forward airstair stowage doorway; and do all
applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, except as
required by paragraph (o)(2) of this AD. Do all applicable related
investigative and corrective actions before further flight. Repeat
the inspections at the applicable times specified in Table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-53-
1058, Revision 4, dated January 9, 2014, until the applicable
terminating action specified in paragraph (m) of this AD is done.
(i) Inspections and Corrective Actions for Group 1 and Group 2
Airplanes That Have a Certain Preventative Modification Installed
For Group 1 and Group 2 airplanes identified in Boeing Service
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, on which a
preventative modification has been installed as specified in any of
the service information identified in paragraphs (i)(1) through
(i)(4) of this AD: Within the applicable times specified in Table 1
of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-
53-1058, Revision 4, dated January 9, 2014, except as required by
paragraph (o)(1) of this AD, do a high frequency eddy current
inspection for cracking of the bear strap of the forward airstair
stowage doorway, a low frequency eddy current inspection for
cracking of the skin assembly and bear strap of the forward airstair
stowage doorway, and detailed inspections for cracking of the skin
assembly and bear strap of the forward airstair stowage doorway; and
do all related investigative and applicable corrective actions; in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 737-53-1058,
[[Page 74602]]
Revision 4, dated January 9, 2014, except as required by paragraph
(o)(2) of this AD. Do all applicable related investigative and
corrective actions before further flight. Repeat the inspections at
the applicable times specified in Table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4,
dated January 9, 2014, until the applicable terminating action
specified in paragraph (m) of this AD is done.
(1) Boeing Service Bulletin 737-53-1058, dated April 4, 1980.
(2) Boeing Service Bulletin 737-53-1058, Revision 1, dated March
5, 1987.
(3) Boeing Service Bulletin 737-53-1058, Revision 2, dated
December 7, 1989.
(4) Boeing Service Bulletin 737-53-1058, Revision 3, dated March
11, 1993.
(j) Inspections and Corrective Actions for Group 3 Through Group 5
Airplanes
For Group 3 through Group 5 airplanes identified in Boeing
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014: At
the applicable times specified in Table 2 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4,
dated January 9, 2014, except as required by paragraph (o)(1) of
this AD, do a high frequency eddy current inspection for cracking of
the bear strap of the forward airstair stowage doorway, a low
frequency eddy current inspection for cracking of the skin assembly
and bear strap of the forward airstair stowage doorway, and detailed
inspections for cracking of the skin assembly and bear strap of the
forward airstair stowage doorway; and do all related investigative
and applicable corrective actions; in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 737-53-1058,
Revision 4, dated January 9, 2014, except as required by paragraph
(o)(2) of this AD. Do all applicable related investigative and
corrective actions before further flight. Repeat the inspections at
the applicable times specified in Table 2 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4,
dated January 9, 2014, until the applicable terminating action
specified in paragraph (m) of this AD is done.
(k) Inspections and Corrective Actions for Group 6 Airplanes
For Group 6 airplanes identified in Boeing Service Bulletin 737-
53-1058, Revision 4, dated January 9, 2014: Within 120 days after
the effective date of this AD, inspect and repair any cracking using
a method approved in accordance with the procedures specified in
paragraph (q) of this AD.
(l) Post-Repair and Post-Modification Inspections for Group 1 and Group
2 Airplanes
For Group 1 and Group 2 airplanes on which any repair has been
done as specified in any of the service information identified in
paragraphs (l)(1) through (l)(3) of this AD, or on which any repair
or modification has been done as specified in the service
information identified in paragraph (l)(4) of this AD: At the
applicable times specified in Table 3 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4,
dated January 9, 2014, except as required by paragraph (o)(1) of
this AD, do a high frequency eddy current inspection for cracking in
the bear strap and skin assembly and a general visual inspection for
cracking in the frame of the forward airstair stowage doorway; or do
low frequency eddy current inspections for cracking of the skin
assembly and bear strap of the forward airstair stowage doorway; in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 737-53-1058, Revision 4, dated January 9, 2014. Options
provided in Boeing Service Bulletin 737-53-1058, Revision 4, dated
January 9, 2014, for accomplishing the inspections are acceptable
for compliance with the corresponding requirements of this paragraph
provided that the inspections are done at the applicable times
specified in paragraph 1.E., ``Compliance,'' of the Boeing Service
Bulletin 737-53-1058, Revision 4, dated January 9, 2014. If any
cracking is found, before further flight, repair the cracking using
a method approved in accordance with the procedures specified in
paragraph (q) of this AD. Repeat the inspections at the applicable
times specified in Table 3 of paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 737-53-1058, Revision 4, dated January 9,
2014.
(1) Boeing Service Bulletin 737-53-1058, Revision 1, dated March
5, 1987.
(2) Boeing Service Bulletin 737-53-1058, Revision 2, dated
December 7, 1989.
(3) Boeing Service Bulletin 737-53-1058, Revision 3, dated March
11, 1993.
(4) Boeing Service Bulletin 737-53-1058, Revision 4, dated
January 9, 2014.
(m) Optional Terminating Actions
(1) For Group 1 and Group 2 airplanes identified in Boeing
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014:
Accomplishment of a repair for cracking of the skin assembly and
bear strap of the forward airstair stowage doorway before the
effective date of this AD, using any service information specified
in paragraphs (m)(1)(i) through (m)(1)(iv) of this AD, terminates
the inspections required by paragraphs (g), (h), and (i) of this AD.
(i) Boeing Service Bulletin 737-53-1058, Revision 1, dated March
5, 1987.
(ii) Boeing Service Bulletin 737-53-1058, Revision 2, dated
December 7, 1989.
(iii) Boeing Service Bulletin 737-53-1058, Revision 3, dated
March 11, 1993.
(iv) Boeing Service Bulletin 737-53-1058, Revision 4, dated
January 9, 2014.
(2) For Group 1 and Group 2 airplanes identified in Boeing
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014:
Accomplishment of a preventative modification for cracking of the
skin assembly and bear strap of the forward airstair stowage doorway
before the effective date of this AD, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 737-53-1058,
Revision 4, dated January 9, 2014, terminates the inspections
required by paragraphs (g), (h), and (i) of this AD.
(3) For Group 3 through Group 5 airplanes identified in Boeing
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014:
Repairing or modifying the forward airstair stowage doorway, in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, terminates
the inspections required by paragraph (j) of this AD.
(4) Accomplishment, prior to the effective date of this AD, of a
repair of the aft lower corner of the forward airstair stowage
doorway that was approved by Boeing Commercial Airplanes
Organization Designation Authorization (ODA) using FAA Form 8100-9,
terminates the inspections required by paragraph (j) of this AD.
(n) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (g), (h), and (i) of this AD, if those actions were
performed before the effective date of this AD using any service
information specified in paragraphs (n)(i) through (n)(iii) of this
AD.
(i) Boeing Service Bulletin 737-53-1058, Revision 1, dated March
5, 1987.
(ii) Boeing Service Bulletin 737-53-1058, Revision 2, dated
December 7, 1989.
(iii) Boeing Service Bulletin 737-53-1058, Revision 3, dated
March 11, 1993.
(o) Exceptions to the Service Information
(1) Where Boeing Service Bulletin 737-53-1058, Revision 4, dated
January 9, 2014, specifies a compliance time ``after the Revision 4
date of this service bulletin,'' this AD requires compliance within
the specified compliance time ``after the effective date of this
AD.''
(2) Where Boeing Service Bulletin 737-53-1058, Revision 4, dated
January 9, 2014, specifies to contact Boeing for repair
instructions: Before further flight, repair using a method approved
in accordance with the procedures specified in paragraph (q) of this
AD.
(p) Post-Repair and Post-Modification Inspections for Group 3 Through
Group 5 Airplanes Not Required
The post-repair and post-modification inspections specified in
Table 4 of paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, are not
required by this AD.
Note 1 to paragraph (p) of this AD: The post-repair and post-
modification inspections specified in Table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4,
dated January 9, 2014, may be used in support of compliance with
section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation
Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)).
(q) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (r)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
[[Page 74603]]
(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 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. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(r) Related Information
(1) For more information about this AD, contact Nenita Odesa,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
CA 90712-4137; phone: (562) 627-5234; fax: (562) 627-5210; email:
nenita.odesa@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (s)(3) and (s)(4) of this AD.
(s) 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 Service Bulletin 737-53-1058, Revision 4, dated
January 9, 2014.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at 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 December 5, 2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-29190 Filed 12-15-14; 8:45 am]
BILLING CODE 4910-13-P
