Airworthiness Directives; The Boeing Company Airplanes, 31389-31394 [2013-10797]
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Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations
time specified in paragraph (m)(1) or (m)(2)
of this AD.
(1) If the inspection is done on or after the
effective date of this AD: Submit the report
within 90 days after doing the inspection.
(2) If the inspection was done prior to the
effective date of this AD: Submit the report
within 90 days after the effective date of this
AD.
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(n) 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1138; fax (425)
227–1149. Information may be emailed to: 9ANM-116-AMOC-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. The AMOC
approval letter must specifically reference
this AD. AMOCs approved previously in
accordance with AD 2010–02–10,
Amendment 39–16181 (75 FR 4477, January
28, 2010), are approved as AMOCs for the
corresponding provisions of this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing, and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
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(o) Special Flight Permits
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed if any crack is
found during any inspection required by this
AD.
(p) Related Information
(1) Refer to mandatory continued
airworthiness information (MCAI) EASA
Airworthiness Directive 2011–0211, dated
October 31, 2011, and the service information
specified in paragraphs (p)(1)(i) through
(p)(1)(vii) of this AD, for related information.
(i) Airbus Mandatory Service Bulletin
A330–32–3220, dated October 10, 2008.
(ii) Airbus Mandatory Service Bulletin
A330–32–3220, Revision 01, dated October 5,
2011.
(iii) Airbus Mandatory Service Bulletin
A330–32–3220, Revision 02, dated December
13, 2012.
(iv) Airbus Mandatory Service Bulletin
A330–32–3248, Revision 01, including
Appendix 01, dated December 13, 2012.
(v) Airbus Mandatory Service Bulletin
A340–32–4264, dated October 10, 2008.
(vi) Airbus Mandatory Service Bulletin
A340–32–4286, dated October 5, 2011.
(vii) Airbus Mandatory Service Bulletin
A340–32–5087, dated October 10, 2008.
(2) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may
review copies of the 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.
(q) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on June 28, 2013.
(i) Airbus Mandatory Service Bulletin
A330–32–3220, Revision 01, dated October 5,
2011.
(ii) Airbus Mandatory Service Bulletin
A330–32–3220, Revision 02, dated December
13, 2012.
(iii) Airbus Mandatory Service Bulletin
A330–32–3248, Revision 01, including
Appendix 01, dated December 13, 2012.
(iv) Airbus Mandatory Service Bulletin
A340–32–4286, dated October 5, 2011.
(4) The following service information was
approved for IBR on March 4, 2010 (75 FR
4477, January 28, 2010).
(i) Airbus Mandatory Service Bulletin
A330–32–3220, dated October 10, 2008.
(ii) Airbus Mandatory Service Bulletin
A340–32–4264, dated October 10, 2008.
(iii) Airbus Mandatory Service Bulletin
A340–32–5087, dated October 10, 2008.
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31389
(5) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(6) You may review copies of the 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.
(7) 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 13,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–11903 Filed 5–23–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0855; Directorate
Identifier 2011–NM–136–AD; Amendment
39–17452; AD 2013–09–10]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
all The Boeing Company Model 737–
100, –200, –200C, –300, –400, and –500
series airplanes. That AD currently
requires repetitive inspections to detect
cracking of the lower corners of the door
frame and cross beam of the forward
cargo door, and corrective actions if
necessary. That AD also requires
eventual modification of the outboard
radius of the lower corners of the door
frame and reinforcement of the cross
beam of the forward cargo door, which
terminates the existing repetitive
inspections. This new AD revises the
compliance times for the preventive
modification; adds certain inspections
for cracks in the number 5 cross beam
of the forward cargo door; and adds
inspections of the number 4 cross beam
if cracks are found in the number 5
cross beam, and corrective actions if
necessary. For certain airplanes, this
SUMMARY:
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new AD also adds a one-time inspection
for airplanes previously modified or
repaired, and a one-time inspection of
the reinforcement angle for excessive
shimming or fastener pull-up, and
corrective actions if necessary. This AD
was prompted by additional reports of
fatigue cracking in the radius of the
lower frames and in the lower number
5 cross beam of the forward cargo door.
We are issuing this AD to prevent
fatigue cracking of the lower corners of
the door frame and number 5 cross
beam of the forward cargo door, which
could result in rapid depressurization of
the airplane.
DATES: This AD is effective June 28,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of June 28, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of May 16, 2000 (65 FR
19302, April 11, 2000).
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
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; 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
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: (425)
917–6450; fax: (425) 917–6590; email:
alan.pohl@faa.gov.
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SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede airworthiness
directive (AD) 2000–07–06, Amendment
39–11660 (65 FR 19302, April 11, 2000).
That AD applies to the specified
products. The NPRM published in the
Federal Register on August 21, 2012 (77
FR 50407). The NPRM proposed to
continue to require repetitive
inspections to detect cracking of the
lower corners of the door frame and
cross beam of the forward cargo door,
and corrective actions if necessary. The
NPRM also proposed to continue to
require eventual modification of the
outboard radius of the lower corners of
the door frame and reinforcement of the
cross beam of the forward cargo door,
which would constitute terminating
action for the existing repetitive
inspections. Additionally, the NPRM
proposed to revise the compliance times
for the preventive modification; add
certain inspections for cracks in the
number 5 cross beam of the forward
cargo door; and add inspections of the
number 4 cross beam if cracks are found
in the number 5 cross beam, and
corrective actions if necessary. For
certain airplanes, the NPRM also
proposed to add a one-time inspection
for airplanes previously modified or
repaired, and a one-time inspection of
the reinforcement angle for excessive
shimming or fastener pull-up, and
corrective actions if necessary.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (77 FR 50407,
August 21, 2012) and the FAA’s
response to each comment.
Comment Regarding Winglet
Supplemental Type Certificate (STC)
Aviation Partners Boeing stated that
installation of winglets per STC
ST01219SE (https://rgl.faa.gov/
regulatory_and_guidance_library/rgstc.
nsf/0/2C6E3DBDDD36F91C862576
A4005D64E2?OpenDocument&
Highlight=st01219se) does not affect the
ability to accomplish the service
information or the NPRM (77 FR 50407,
August 21, 2012).
We have revised paragraph (c) in this
final rule, by adding new paragraph
(c)(2), to state that installation of STC
ST01219SE (https://rgl.faa.gov/
regulatory_and_guidance_library/
rgstc.nsf/0/2C6E3DBDDD36F9
1C862576A4005D64E2?Open
Document&Highlight=st01219se) does
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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’’
AMOC approval request is not necessary
to comply with the requirements of 14
CFR 39.17. For all other AMOC
requests, however, the operator must
request approval for an AMOC in
accordance with the procedures
specified in paragraph (n) of this AD.
Request To Add New Requirements
Boeing asked that we add a new
paragraph (k) to the NPRM (77 FR
50407, August 21, 2012) titled ‘‘New
Inspections and Corrective Actions to
Ensure Cross Beam Reinforcement,’’ and
suggested language for that new
requirement. Boeing stated that the
intent of the NPRM and Boeing Alert
Service Bulletin 737–52A1100, Revision
5, dated February 14, 2011, is to ensure
that all forward cargo doors have the
reinforcing modifications installed on
both the beam and the frame at the
forward and aft lower corners of the
door. Boeing added that the current
language in the NPRM and this service
information leave open the potential
that some doors might not have the
reinforcing modification on the aft end
of the cross beam, even though the
doors were modified as specified in
Boeing Service Bulletin 737–52–1100,
dated August 25, 1988, or Revision 1,
dated July 20, 1989; or in accordance
with the requirements of AD 90–06–02,
Amendment 39–6489 (55 FR 8372,
March 7, 1990).
We do not agree with the commenter’s
request to add a new requirement to this
AD. Boeing Service Bulletin 737–52–
1100, dated August 25, 1988; and
Revision 1, dated July 20, 1989;
includes modifications of the forward
corner of the door frame and forward
end of the lower cross beam, but no
modifications of the aft end of the door.
Modifications of the aft corner of the
door frame and aft end of the lower
cross beam were added in Boeing
Service Bulletin 737–52–1100, Revision
2, dated March 31, 1994. Boeing Service
Bulletin 737–52–1100, Revision 2, dated
March 31, 1994, was required by
paragraph (c) of AD 2000–07–06,
Amendment 39–11660 (65 FR 19302,
April 11, 2000), as terminating action
for the repetitive inspections. Paragraph
(c) of AD 2000–07–06 is restated in
paragraph (i) of this AD, and addresses
airplanes on which no modification was
accomplished previously.
The intent of paragraph (d) of AD
2000–07–06, Amendment 39–11660 (65
FR 19302, April 11, 2000), which is
restated in paragraph (j) of this AD, was
to address airplanes on which a
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modification was previously
accomplished in accordance with
Boeing Service Bulletin 737–52–1100,
dated August 25, 1988; or Revision 1,
dated July 20, 1989; and to ensure that
both the forward and aft ends of the
lower beam of the door were modified,
as well as the forward and aft corners of
the door frame. Therefore, Boeing
Service Bulletin 737–52–1100, Revision
2, dated March 31, 1994, was required
by AD 2000–07–06 for those
modifications. However, paragraph (d)
of AD 2000–07–06 and paragraph (j) of
this AD do not specify modifying the aft
end of the lower beam.
We have made no change to the AD
in regard to Boeing’s request. However,
we are considering proposing additional
rulemaking in the near future to address
this issue.
Explanation of Change to Final Rule
We have changed paragraph (g) of this
final rule to specify performing the
inspection in accordance with Boeing
737 Nondestructive Test (NDT) Manual,
D6–37239, Part 6, Section 51–00–00,
Procedure 4 or Procedure 23, Revision
108, dated November 15, 2012, as
applicable. The subject procedures were
referred to as figures in the NPRM (77
FR 50407, August 21, 2012). Because of
a publishing system change in this
revision of the NDT manual, the term
‘‘figure’’ was changed to ‘‘procedure.’’
The technical instructions in the NDT
manual were not changed.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
We also determined that this change
will not increase the economic burden
on any operator or increase the scope of
the AD.
Costs of Compliance
We estimate that this AD affects 581
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspections retained from AD
2000–07–06, Amendment
39–11660 (65 FR 19302,
April 11, 2000).
Modification retained from AD
2000–07–06.
Inspections, new action ..........
We estimate the following costs to do
any necessary modifications that would
$85 per inspection cycle ........
$49,385 per inspection cycle.
$1,865
$3,395 ....................................
$1,972,495.
$0
18 work-hours × $85 per hour
= $1,530.
9 work-hours × $85 per hour
= $765.
Cost on U.S.
operators
$0
1 work-hour × $85 per hour =
$85 per inspection cycle.
Cost per product
$765 .......................................
$444,465.
Parts cost
be required based on the results of the
inspections. We have no way of
determining the number of aircraft that
might need these modifications:
ON-CONDITION COSTS
Action
Labor cost
Modification ...................................................................
84 work-hours × $85 per hour = $7,140 ......................
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition repairs/
replacements specified in this AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
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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
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
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Parts cost
$12,395
Cost per
product
$19,535
(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
removing airworthiness directive (AD)
2000–07–06, Amendment 39–11660 (65
FR 19302, April 11, 2000), and adding
the following new AD:
■
2013–09–10 The Boeing Company:
Amendment 39–17452; Docket No.
FAA–2012–0855; Directorate Identifier
2011–NM–136–AD.
(a) Effective Date
This AD is effective June 28, 2013.
(b) Affected ADs
This AD supersedes AD 2000–07–06,
Amendment 39–11660 (65 FR 19302, April
11, 2000).
(c) Applicability
(1) This AD applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://rgl.faa.
gov/regulatory_and_guidance_library/rgstc
.nsf/0/2C6E3DBDDD36F91C862576A40
05D64E2?OpenDocument&Highlight=
st01219se) 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
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 52, Doors.
(e) Unsafe Condition
This AD was prompted by additional
reports of fatigue cracking in the radius of the
lower frames and in the lower number 5
cross beam of the forward cargo door. We are
issuing this AD to prevent fatigue cracking of
the lower corners of the door frame and
number 5 cross beam of the forward cargo
door, which could result in rapid
depressurization of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained High Frequency Eddy Current
(HFEC) Initial/Repetitive Inspections
This paragraph restates the requirements of
paragraph (a) of AD 2000–07–06,
Amendment 39–11660 (65 FR 19302, April
11, 2000), with revised service information.
Within 1 year or 4,500 flight cycles after May
16, 2000 (the effective date of AD 2000–07–
06), whichever occurs later, perform an HFEC
inspection to detect cracking of the lower
corners (forward and aft) of the door frame
of the forward cargo door, in accordance with
Figure 4 or Figure 23, of Section 51–00–00,
of Part 6, of Boeing 737 Nondestructive Test
(NDT) Manual, D6–37239, dated August 5,
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1997, as applicable; or Procedure 4 or
Procedure 23, of Section 51–00–00, of Part 6,
of Boeing 737 Nondestructive Test (NDT)
Manual, D6–37239, Revision 108, dated
November 15, 2012; as applicable.
Note 1 to paragraphs (g), (h), (i), and (j) of
this AD: Accomplishment of Boeing Service
Bulletin 737–52–1100, Revision 2, dated
March 31, 1994, does not supersede the
requirements of AD 90–06–02, Amendment
39–6489 (55 FR 8372, March 7, 1990).
(1) If no cracking is detected, repeat the
HFEC inspection thereafter at intervals not to
exceed 4,500 flight cycles, until the
requirements of paragraph (i) of this AD have
been accomplished.
(2) If any cracking is detected during any
inspection required by paragraph (g) of this
AD, prior to further flight, accomplish the
requirements of paragraphs (g)(2)(i) and
(g)(2)(ii) of this AD, which constitute
terminating action for the repetitive
inspections required by paragraph (g)(1) of
this AD.
(i) Accomplish the requirements of
paragraph (g)(2)(i)(A) or (g)(2)(i)(B) of this
AD, and install a cross beam repair and
reinforcement modification of the cross
beam, in accordance with Boeing Service
Bulletin 737–52–1100, Revision 2, dated
March 31, 1994.
(A) Repair the door frame of the forward
cargo door in accordance with a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), Transport
Airplane Directorate, FAA; or in accordance
with data meeting the type certification basis
of the airplane approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make such findings. For a repair or
modification method to be approved by the
Manager, Seattle ACO, as required by this
paragraph, and paragraphs (g)(2)(ii), (h)(2),
(h)(3)(ii), and (i)(2) of this AD, the Manager’s
approval letter must specifically reference
this AD.
(B) Replace the door frame of the forward
cargo door with a new door frame, in
accordance with Boeing Service Bulletin
737–52–1100, Revision 2, dated March 31,
1994.
(ii) Modify the repaired or replaced door
frame of the forward cargo door, in
accordance with a method approved by the
Manager, Seattle ACO, or in accordance with
data meeting the type certification basis of
the airplane approved by the Boeing
Commercial Airplanes ODA that has been
authorized by the Manager, Seattle ACO, to
make those findings.
(h) Retained Initial Detailed Inspection and
Repetitive Inspections
This paragraph restates the requirements of
paragraph (b) of AD 2000–07–06,
Amendment 39–11660 (65 FR 19302, April
11, 2000). Within 1 year or 4,500 flight cycles
after May 16, 2000 (the effective date of AD
2000–07–06), whichever occurs later,
perform a detailed inspection to detect
cracking of the cross beam (i.e., upper and
lower chord and web sections) of the forward
cargo door, in accordance with Boeing
Service Bulletin 737–52–1100, Revision 2,
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dated March 31, 1994. For the purposes of
this AD, a detailed inspection is: An
intensive examination of a specific item,
installation, or assembly to detect damage,
failure, or irregularity. Available lighting is
normally supplemented with a direct source
of good lighting at an intensity deemed
appropriate. Inspection aids such as mirror,
magnifying lenses, etc., may be necessary.
Surface cleaning and elaborate procedures
may be required.
(1) If no cracking is detected, repeat the
inspection thereafter at intervals not to
exceed 4,500 flight cycles until the
requirements of paragraph (i) of this AD have
been accomplished.
(2) If any cracking is detected on the lower
chord section of the cross beam during any
inspection required by paragraph (h) of this
AD, prior to further flight, repair in
accordance with a method approved by the
Manager, Seattle ACO, or in accordance with
data meeting the type certification basis of
the airplane approved by the Boeing
Commercial Airplanes ODA that has been
authorized by the Manager, Seattle ACO, to
make those findings.
(3) If any cracking is detected on any area
excluding the lower chord section of the
cross beam (i.e., upper chord and web
section) during any inspection required by
paragraph (h) of this AD, prior to further
flight, accomplish the requirements of
paragraph (h)(3)(i) or (h)(3)(ii) of this AD, as
applicable, which constitutes terminating
action for the repetitive inspections required
by paragraph (h)(1) of this AD.
(i) For airplanes with line numbers 1
through 1231 inclusive: Install a cross beam
repair and preventative modification of the
outboard radius of the lower corners (forward
and aft) of the door frame, in accordance with
Boeing Service Bulletin 737–52–1100,
Revision 2, dated March 31, 1994.
(ii) For airplanes with line numbers 1232
and subsequent: Install a cross beam repair
and preventative modification of the
outboard radius of the lower corners (forward
and aft) of the door frame, in accordance with
a method approved by the Manager, Seattle
ACO, or in accordance with data meeting the
type certification basis of the airplane
approved by the Boeing Commercial
Airplanes ODA that has been authorized by
the Manager, Seattle ACO, to make those
findings.
(i) Retained Terminating Action
This paragraph restates the requirements of
paragraph (c) of AD 2000–07–06,
Amendment 39–11660 (65 FR 19302, April
11, 2000), with revised service information.
Within 4 years or 12,000 flight cycles after
May 16, 2000 (the effective date of AD 2000–
07–06), whichever occurs later: Install the
preventative modification of the outboard
radius of the lower corners (forward and aft)
of the door frame and the reinforcement
modification of the cross beam of the forward
cargo door, in accordance with paragraph
(i)(1) or (i)(2) of this AD, as applicable.
Accomplishment of paragraph (i)(1) or (i)(2)
of this AD, as applicable, constitutes
terminating action for the repetitive
inspections required by paragraphs (g)(1) and
(h)(1) of this AD.
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(1) For airplanes with line numbers 1
through 1231 inclusive: Accomplish the
preventative modification and the
reinforcement modification, in accordance
with Boeing Service Bulletin 737–52–1100,
Revision 2, dated March 31, 1994.
(2) For airplanes with line numbers 1232
and subsequent: Accomplish the preventative
modification and the reinforcement
modification, in accordance with a method
approved by the Manager, Seattle ACO, or in
accordance with data meeting the type
certification basis of the airplane approved
by the Boeing Commercial Airplanes ODA
that has been authorized by the Manager,
Seattle ACO, to make those findings; or in
accordance with Boeing Alert Service
Bulletin 737–52A1100, Revision 5, dated
February 14, 2011. As of the effective date of
this AD, use only Boeing Alert Service
Bulletin 737–52A1100, Revision 5, dated
February 14, 2011, to accomplish the
modifications required by this paragraph.
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(j) Retained Action for Airplanes on Which
Modifications Were Accomplished
Previously
This paragraph restates the requirements of
paragraph (d) of AD 2000–07–06,
Amendment 39–11660 (65 FR 19302, April
11, 2000). For all airplanes on which
modifications of the forward lower corner of
the door frame and the cross beam of the
forward cargo door were accomplished as
specified in Boeing Service Bulletin 737–52–
1100, dated August 25, 1988, or Revision 1,
dated July 20, 1989; or in accordance with
the requirements of AD 90–06–02,
Amendment 39–6489 (55 FR 8372, March 7,
1990): Within 4 years or 12,000 flight cycles
after May 16, 2000 (the effective date of AD
2000–07–06), whichever occurs later, install
the reinforcement modification of the aft
corner of the door frame of the forward cargo
door, in accordance with Boeing Service
Bulletin 737–52–1100, Revision 2, dated
March 31, 1994. Accomplishment of such
modification constitutes terminating action
for the repetitive inspections required by
paragraphs (g)(1) and (h)(1) of this AD.
(k) New Inspections and Corrective Actions
Except as provided by paragraphs (m)(1)
and (m)(2) of this AD: At the applicable time
specified in paragraph 1.E, ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–52A1100,
Revision 5, dated February 14, 2011, do the
inspections required by paragraphs (k)(1) and
(k)(2) of this AD, as applicable. Do all
applicable related investigative and
corrective actions before further flight, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–52A1100, Revision 5, dated February 14,
2011; except as required by paragraph (m)(3)
of this AD. Accomplishment of the
inspections required by paragraph (k) of this
AD terminates the requirements of the
repetitive inspections required by paragraphs
(g)(1) and (h)(1) of this AD. If any cracking
is found in the number 4 cross beam, before
further flight, repair in accordance with
Boeing Special Attention Service Bulletin
737–52–1149, dated December 11, 2003.
Note 2 to paragraph (k) of this AD: Boeing
Alert Service Bulletin 737–52A1100,
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17:44 May 23, 2013
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Revision 5, dated February 14, 2011, refers to
Boeing Special Attention Service Bulletin
737–52–1149, dated December 11, 2003, as
an additional source of guidance for the
inspection for cracks of the number 4 cross
beam.
(1) For airplanes identified in Tables 1 and
2 of paragraph 1.E, ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–52A1100,
Revision 5, dated February 14, 2011: Do a
one-time HFEC inspection of the applicable
location for cracks, in accordance with the
Work Instructions, Part I, of Boeing Alert
Service Bulletin 737–52A1100, Revision 5,
dated February 14, 2011.
(2) For airplanes identified in Table 3 of
paragraph 1.E, ‘‘Compliance,’’ of Boeing Alert
Service Bulletin 737–52A1100, Revision 5,
dated February 14, 2011: Do a one-time
general visual inspection of the
reinforcement angle for excessive shimming
or fastener pull-up, in accordance with the
Work Instructions, Part III, of Boeing Alert
Service Bulletin 737–52A1100, Revision 5,
dated February 14, 2011.
(l) No Supplemental Structural Inspections
Required by This AD
(1) The supplemental structural
inspections specified in Table 4 of paragraph
1.E., ‘‘Compliance,’’ and Part 5 of the
Accomplishment Instructions, of Boeing
Alert Service Bulletin 737–52A1100,
Revision 5, dated February 14, 2011, are not
required by this AD.
(2) The supplemental structural
inspections specified in Table 4 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–52A1100, Revision 5, dated
February 14, 2011, 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)). The corresponding actions
specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–52A1100, Revision 5, dated February 14,
2011, are not required by this AD.
(m) Exceptions to Certain Service
Information
(1) Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–52A1100,
Revision 5, dated February 14, 2011,
specifies a compliance time relative to the
Revision 5 issue date of that service bulletin,
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
(2) Where Table 1, ‘‘Condition’’ column of
Paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–52A1100,
Revision 5, dated February 14, 2011,
specifies ‘‘airplanes without either the repair
or modification accomplished in accordance
with previous releases of this service
bulletin,’’ the corresponding condition in this
AD is for ‘‘airplanes on which either a repair
or modification was not accomplished before
the effective date of this AD.’’
(3) Where Boeing Alert Service Bulletin
737–52A1100, Revision 5, dated February 14,
2011, specifies to contact Boeing for certain
actions: Before further flight, do the repair
using a method approved in accordance with
the procedures specified in paragraph (n)(1)
of this AD.
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
31393
(n) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO, 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 the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-ACO–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
required by this AD if it is approved by the
Boeing Commercial Airplanes 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.
(4) AMOCs approved previously in
accordance with AD 2000–07–06,
Amendment 39–11660 (65 FR 19302, April
11, 2000), are approved as AMOCs for the
corresponding requirements of this AD.
(o) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone (425) 917–
6450; fax (425) 917–6590; email
alan.pohl@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com. You may review
copies of the referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington.
For information on the availability of this
material at the FAA, call 425–227–1221.
(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.
(3) The following service information was
approved for IBR on June 28, 2013.
(i) Procedure 4, ‘‘Surface Inspection of
Aluminum Parts (Meter Display),’’ of Section
51–00–00, of Part 6, ‘‘Eddy Current,’’ of
Boeing 737 Nondestructive Test (NDT)
Manual, D6–37239, Revision 108, dated
November 15, 2012. The revision level of this
document is identified only in the letter of
transmittal; no other page of this document
contains this information.
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mstockstill on DSK4VPTVN1PROD with RULES
(ii) Procedure 23, ‘‘Aluminum Part Surface
Inspection (Impedance Plane Display),’’
Section 51–00–00, of Part 6, ‘‘Eddy Current,’’
of Boeing 737 Nondestructive Test (NDT)
Manual, D6–37239, Revision 108, dated
November 15, 2012. The revision level of this
document is identified only in the letter of
transmittal; no other page of this document
contains this information.
(iii) Boeing Alert Service Bulletin 737–
52A1100, Revision 5, dated February 14,
2011.
(iv) Boeing Special Attention Service
Bulletin 737–52–1149, dated December 11,
2003.
(4) The following service information was
approved for IBR on May 16, 2000 (65 FR
19302, April 11, 2000).
(i) Figure 4, of Section 51–00–00, of Part
6, of Boeing 737 Nondestructive Test (NDT)
Manual, D6–37239, dated August 5, 1997.
The revision level is not specified on the title
page or list of effective pages of this
document. The title page of this document is
not dated. Pages 1 and 2 of the list of
effective pages of this document are dated
August 5, 1997; page 2A is dated February 5,
1997.
(ii) Figure 23, of Section 51–00–00, of Part
6, of Boeing 737 Nondestructive Test (NDT)
Manual, D6–37239, dated August 5, 1997.
The revision level is not specified on the title
page or list of effective pages of this
document. The title page of this document is
not dated. Pages 1 and 2 of the list of
effective pages of this document are dated
August 5, 1997; page 2A is dated February 5,
1997.
(iii) Boeing Service Bulletin 737–52–1100,
Revision 2, dated March 31, 1994.
(5) For Boeing 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.
(6) You may view this service information
at FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356. For information on
the availability of this material at the FAA,
call 425–227–1221.
(7) 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 April 26,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–10797 Filed 5–23–13; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
17:44 May 23, 2013
Jkt 229001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0445; Directorate
Identifier 2012–SW–098–AD; Amendment
39–17458; AD 2013–10–05]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
Deutschland GmbH Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Eurocopter Deutschland GmbH (ECD)
Model MBB–BK 117 C–2 helicopters.
This AD requires revising the operating
limitations to prohibit flights under
instrument flight rules (IFR) or under
night visual flight rules (VFR) when the
autotrim is inoperative. The actions of
this AD are intended to prevent a
workload situation whereby stabilizing
the helicopter in flight would be
difficult if not impossible, resulting in
possible loss of helicopter control.
DATES: This AD becomes effective June
10, 2013.
We must receive comments on this
AD by July 23, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the economic
evaluation, any comments received, and
other information. The street address for
the Docket Operations Office (telephone
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
PO 00000
Frm 00028
Fmt 4700
Sfmt 4700
For service information identified in
this AD, contact American Eurocopter
Corporation, 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax
(972) 641–3775; or at https://
www.eurocopter.com/techpub. You may
review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT:
George Schwab, Aviation Safety
Engineer, Safety Management Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
george.schwab@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments prior to it becoming effective.
However, we invite you to participate in
this rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that resulted from
adopting this AD. The most helpful
comments reference a specific portion of
the AD, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit them only one time. We will file
in the docket all comments that we
receive, as well as a report summarizing
each substantive public contact with
FAA personnel concerning this
rulemaking during the comment period.
We will consider all the comments we
receive and may conduct additional
rulemaking based on those comments.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, issued EASA AD No. 2012–0216,
dated October 18, 2012, to correct an
unsafe condition for ECD Model MBB–
BK 117 C–2 helicopters. EASA advises
that the autopilot (AP) of a Model MBB–
BK 117 C–2 helicopter failed in flight
with ‘‘ACTUATOR’’ and ‘‘BACKUP
SAS’’ messages appearing on the
caution and advisory display, ‘‘AP’’
illuminated in red on the warning unit,
and Y (Yaw actuator) and P (pitch
actuator) on the primary flight display.
E:\FR\FM\24MYR1.SGM
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]]>Agencies
[Federal Register Volume 78, Number 101 (Friday, May 24, 2013)]
[Rules and Regulations]
[Pages 31389-31394]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-10797]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0855; Directorate Identifier 2011-NM-136-AD;
Amendment 39-17452; AD 2013-09-10]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and
-500 series airplanes. That AD currently requires repetitive
inspections to detect cracking of the lower corners of the door frame
and cross beam of the forward cargo door, and corrective actions if
necessary. That AD also requires eventual modification of the outboard
radius of the lower corners of the door frame and reinforcement of the
cross beam of the forward cargo door, which terminates the existing
repetitive inspections. This new AD revises the compliance times for
the preventive modification; adds certain inspections for cracks in the
number 5 cross beam of the forward cargo door; and adds inspections of
the number 4 cross beam if cracks are found in the number 5 cross beam,
and corrective actions if necessary. For certain airplanes, this
[[Page 31390]]
new AD also adds a one-time inspection for airplanes previously
modified or repaired, and a one-time inspection of the reinforcement
angle for excessive shimming or fastener pull-up, and corrective
actions if necessary. This AD was prompted by additional reports of
fatigue cracking in the radius of the lower frames and in the lower
number 5 cross beam of the forward cargo door. We are issuing this AD
to prevent fatigue cracking of the lower corners of the door frame and
number 5 cross beam of the forward cargo door, which could result in
rapid depressurization of the airplane.
DATES: This AD is effective June 28, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of June 28, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 16,
2000 (65 FR 19302, April 11, 2000).
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. 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; 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 Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 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 to supersede airworthiness directive (AD) 2000-07-06, Amendment
39-11660 (65 FR 19302, April 11, 2000). That AD applies to the
specified products. The NPRM published in the Federal Register on
August 21, 2012 (77 FR 50407). The NPRM proposed to continue to require
repetitive inspections to detect cracking of the lower corners of the
door frame and cross beam of the forward cargo door, and corrective
actions if necessary. The NPRM also proposed to continue to require
eventual modification of the outboard radius of the lower corners of
the door frame and reinforcement of the cross beam of the forward cargo
door, which would constitute terminating action for the existing
repetitive inspections. Additionally, the NPRM proposed to revise the
compliance times for the preventive modification; add certain
inspections for cracks in the number 5 cross beam of the forward cargo
door; and add inspections of the number 4 cross beam if cracks are
found in the number 5 cross beam, and corrective actions if necessary.
For certain airplanes, the NPRM also proposed to add a one-time
inspection for airplanes previously modified or repaired, and a one-
time inspection of the reinforcement angle for excessive shimming or
fastener pull-up, and corrective actions if necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 50407, August 21, 2012) and the FAA's response to each comment.
Comment Regarding Winglet Supplemental Type Certificate (STC)
Aviation Partners Boeing stated that installation of winglets per
STC ST01219SE (https://rgl.faa.gov/regulatory_and_guidance_library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se) does
not affect the ability to accomplish the service information or the
NPRM (77 FR 50407, August 21, 2012).
We have revised paragraph (c) in this final rule, by adding new
paragraph (c)(2), to state that installation of STC ST01219SE (https://rgl.faa.gov/regulatory_and_guidance_library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se) 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'' AMOC approval request is not necessary to comply
with the requirements of 14 CFR 39.17. For all other AMOC requests,
however, the operator must request approval for an AMOC in accordance
with the procedures specified in paragraph (n) of this AD.
Request To Add New Requirements
Boeing asked that we add a new paragraph (k) to the NPRM (77 FR
50407, August 21, 2012) titled ``New Inspections and Corrective Actions
to Ensure Cross Beam Reinforcement,'' and suggested language for that
new requirement. Boeing stated that the intent of the NPRM and Boeing
Alert Service Bulletin 737-52A1100, Revision 5, dated February 14,
2011, is to ensure that all forward cargo doors have the reinforcing
modifications installed on both the beam and the frame at the forward
and aft lower corners of the door. Boeing added that the current
language in the NPRM and this service information leave open the
potential that some doors might not have the reinforcing modification
on the aft end of the cross beam, even though the doors were modified
as specified in Boeing Service Bulletin 737-52-1100, dated August 25,
1988, or Revision 1, dated July 20, 1989; or in accordance with the
requirements of AD 90-06-02, Amendment 39-6489 (55 FR 8372, March 7,
1990).
We do not agree with the commenter's request to add a new
requirement to this AD. Boeing Service Bulletin 737-52-1100, dated
August 25, 1988; and Revision 1, dated July 20, 1989; includes
modifications of the forward corner of the door frame and forward end
of the lower cross beam, but no modifications of the aft end of the
door. Modifications of the aft corner of the door frame and aft end of
the lower cross beam were added in Boeing Service Bulletin 737-52-1100,
Revision 2, dated March 31, 1994. Boeing Service Bulletin 737-52-1100,
Revision 2, dated March 31, 1994, was required by paragraph (c) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), as
terminating action for the repetitive inspections. Paragraph (c) of AD
2000-07-06 is restated in paragraph (i) of this AD, and addresses
airplanes on which no modification was accomplished previously.
The intent of paragraph (d) of AD 2000-07-06, Amendment 39-11660
(65 FR 19302, April 11, 2000), which is restated in paragraph (j) of
this AD, was to address airplanes on which a
[[Page 31391]]
modification was previously accomplished in accordance with Boeing
Service Bulletin 737-52-1100, dated August 25, 1988; or Revision 1,
dated July 20, 1989; and to ensure that both the forward and aft ends
of the lower beam of the door were modified, as well as the forward and
aft corners of the door frame. Therefore, Boeing Service Bulletin 737-
52-1100, Revision 2, dated March 31, 1994, was required by AD 2000-07-
06 for those modifications. However, paragraph (d) of AD 2000-07-06 and
paragraph (j) of this AD do not specify modifying the aft end of the
lower beam.
We have made no change to the AD in regard to Boeing's request.
However, we are considering proposing additional rulemaking in the near
future to address this issue.
Explanation of Change to Final Rule
We have changed paragraph (g) of this final rule to specify
performing the inspection in accordance with Boeing 737 Nondestructive
Test (NDT) Manual, D6-37239, Part 6, Section 51-00-00, Procedure 4 or
Procedure 23, Revision 108, dated November 15, 2012, as applicable. The
subject procedures were referred to as figures in the NPRM (77 FR
50407, August 21, 2012). Because of a publishing system change in this
revision of the NDT manual, the term ``figure'' was changed to
``procedure.'' The technical instructions in the NDT manual were not
changed.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the change described previously. We also determined that
this change will not increase the economic burden on any operator or
increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 581 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
----------------------------------------------------------------------------------------------------------------
Inspections retained from AD 2000- 1 work-hour x $85 $0 $85 per inspection $49,385 per
07-06, Amendment 39-11660 (65 FR per hour = $85 per cycle. inspection cycle.
19302, April 11, 2000). inspection cycle.
Modification retained from AD 18 work-hours x $85 $1,865 $3,395............. $1,972,495.
2000-07-06. per hour = $1,530.
Inspections, new action.......... 9 work-hours x $85 $0 $765............... $444,465.
per hour = $765.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary modifications
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
modifications:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Modification.................................. 84 work-hours x $85 per hour = $12,395 $19,535
$7,140.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs/replacements specified in
this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We 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 the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
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:
[[Page 31392]]
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)
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), and
adding the following new AD:
2013-09-10 The Boeing Company: Amendment 39-17452; Docket No. FAA-
2012-0855; Directorate Identifier 2011-NM-136-AD.
(a) Effective Date
This AD is effective June 28, 2013.
(b) Affected ADs
This AD supersedes AD 2000-07-06, Amendment 39-11660 (65 FR
19302, April 11, 2000).
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in
any category.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/regulatory_and_guidance_library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se)
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
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 52, Doors.
(e) Unsafe Condition
This AD was prompted by additional reports of fatigue cracking
in the radius of the lower frames and in the lower number 5 cross
beam of the forward cargo door. We are issuing this AD to prevent
fatigue cracking of the lower corners of the door frame and number 5
cross beam of the forward cargo door, which could result in rapid
depressurization of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained High Frequency Eddy Current (HFEC) Initial/Repetitive
Inspections
This paragraph restates the requirements of paragraph (a) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), with
revised service information. Within 1 year or 4,500 flight cycles
after May 16, 2000 (the effective date of AD 2000-07-06), whichever
occurs later, perform an HFEC inspection to detect cracking of the
lower corners (forward and aft) of the door frame of the forward
cargo door, in accordance with Figure 4 or Figure 23, of Section 51-
00-00, of Part 6, of Boeing 737 Nondestructive Test (NDT) Manual,
D6-37239, dated August 5, 1997, as applicable; or Procedure 4 or
Procedure 23, of Section 51-00-00, of Part 6, of Boeing 737
Nondestructive Test (NDT) Manual, D6-37239, Revision 108, dated
November 15, 2012; as applicable.
Note 1 to paragraphs (g), (h), (i), and (j) of this AD:
Accomplishment of Boeing Service Bulletin 737-52-1100, Revision 2,
dated March 31, 1994, does not supersede the requirements of AD 90-
06-02, Amendment 39-6489 (55 FR 8372, March 7, 1990).
(1) If no cracking is detected, repeat the HFEC inspection
thereafter at intervals not to exceed 4,500 flight cycles, until the
requirements of paragraph (i) of this AD have been accomplished.
(2) If any cracking is detected during any inspection required
by paragraph (g) of this AD, prior to further flight, accomplish the
requirements of paragraphs (g)(2)(i) and (g)(2)(ii) of this AD,
which constitute terminating action for the repetitive inspections
required by paragraph (g)(1) of this AD.
(i) Accomplish the requirements of paragraph (g)(2)(i)(A) or
(g)(2)(i)(B) of this AD, and install a cross beam repair and
reinforcement modification of the cross beam, in accordance with
Boeing Service Bulletin 737-52-1100, Revision 2, dated March 31,
1994.
(A) Repair the door frame of the forward cargo door in
accordance with a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), Transport Airplane Directorate, FAA; or
in accordance with data meeting the type certification basis of the
airplane approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make such findings. For a repair or
modification method to be approved by the Manager, Seattle ACO, as
required by this paragraph, and paragraphs (g)(2)(ii), (h)(2),
(h)(3)(ii), and (i)(2) of this AD, the Manager's approval letter
must specifically reference this AD.
(B) Replace the door frame of the forward cargo door with a new
door frame, in accordance with Boeing Service Bulletin 737-52-1100,
Revision 2, dated March 31, 1994.
(ii) Modify the repaired or replaced door frame of the forward
cargo door, in accordance with a method approved by the Manager,
Seattle ACO, or in accordance with data meeting the type
certification basis of the airplane approved by the Boeing
Commercial Airplanes ODA that has been authorized by the Manager,
Seattle ACO, to make those findings.
(h) Retained Initial Detailed Inspection and Repetitive Inspections
This paragraph restates the requirements of paragraph (b) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000). Within
1 year or 4,500 flight cycles after May 16, 2000 (the effective date
of AD 2000-07-06), whichever occurs later, perform a detailed
inspection to detect cracking of the cross beam (i.e., upper and
lower chord and web sections) of the forward cargo door, in
accordance with Boeing Service Bulletin 737-52-1100, Revision 2,
dated March 31, 1994. For the purposes of this AD, a detailed
inspection is: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or
irregularity. Available lighting is normally supplemented with a
direct source of good lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying lenses, etc., may be
necessary. Surface cleaning and elaborate procedures may be
required.
(1) If no cracking is detected, repeat the inspection thereafter
at intervals not to exceed 4,500 flight cycles until the
requirements of paragraph (i) of this AD have been accomplished.
(2) If any cracking is detected on the lower chord section of
the cross beam during any inspection required by paragraph (h) of
this AD, prior to further flight, repair in accordance with a method
approved by the Manager, Seattle ACO, or in accordance with data
meeting the type certification basis of the airplane approved by the
Boeing Commercial Airplanes ODA that has been authorized by the
Manager, Seattle ACO, to make those findings.
(3) If any cracking is detected on any area excluding the lower
chord section of the cross beam (i.e., upper chord and web section)
during any inspection required by paragraph (h) of this AD, prior to
further flight, accomplish the requirements of paragraph (h)(3)(i)
or (h)(3)(ii) of this AD, as applicable, which constitutes
terminating action for the repetitive inspections required by
paragraph (h)(1) of this AD.
(i) For airplanes with line numbers 1 through 1231 inclusive:
Install a cross beam repair and preventative modification of the
outboard radius of the lower corners (forward and aft) of the door
frame, in accordance with Boeing Service Bulletin 737-52-1100,
Revision 2, dated March 31, 1994.
(ii) For airplanes with line numbers 1232 and subsequent:
Install a cross beam repair and preventative modification of the
outboard radius of the lower corners (forward and aft) of the door
frame, in accordance with a method approved by the Manager, Seattle
ACO, or in accordance with data meeting the type certification basis
of the airplane approved by the Boeing Commercial Airplanes ODA that
has been authorized by the Manager, Seattle ACO, to make those
findings.
(i) Retained Terminating Action
This paragraph restates the requirements of paragraph (c) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), with
revised service information. Within 4 years or 12,000 flight cycles
after May 16, 2000 (the effective date of AD 2000-07-06), whichever
occurs later: Install the preventative modification of the outboard
radius of the lower corners (forward and aft) of the door frame and
the reinforcement modification of the cross beam of the forward
cargo door, in accordance with paragraph (i)(1) or (i)(2) of this
AD, as applicable. Accomplishment of paragraph (i)(1) or (i)(2) of
this AD, as applicable, constitutes terminating action for the
repetitive inspections required by paragraphs (g)(1) and (h)(1) of
this AD.
[[Page 31393]]
(1) For airplanes with line numbers 1 through 1231 inclusive:
Accomplish the preventative modification and the reinforcement
modification, in accordance with Boeing Service Bulletin 737-52-
1100, Revision 2, dated March 31, 1994.
(2) For airplanes with line numbers 1232 and subsequent:
Accomplish the preventative modification and the reinforcement
modification, in accordance with a method approved by the Manager,
Seattle ACO, or in accordance with data meeting the type
certification basis of the airplane approved by the Boeing
Commercial Airplanes ODA that has been authorized by the Manager,
Seattle ACO, to make those findings; or in accordance with Boeing
Alert Service Bulletin 737-52A1100, Revision 5, dated February 14,
2011. As of the effective date of this AD, use only Boeing Alert
Service Bulletin 737-52A1100, Revision 5, dated February 14, 2011,
to accomplish the modifications required by this paragraph.
(j) Retained Action for Airplanes on Which Modifications Were
Accomplished Previously
This paragraph restates the requirements of paragraph (d) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000). For
all airplanes on which modifications of the forward lower corner of
the door frame and the cross beam of the forward cargo door were
accomplished as specified in Boeing Service Bulletin 737-52-1100,
dated August 25, 1988, or Revision 1, dated July 20, 1989; or in
accordance with the requirements of AD 90-06-02, Amendment 39-6489
(55 FR 8372, March 7, 1990): Within 4 years or 12,000 flight cycles
after May 16, 2000 (the effective date of AD 2000-07-06), whichever
occurs later, install the reinforcement modification of the aft
corner of the door frame of the forward cargo door, in accordance
with Boeing Service Bulletin 737-52-1100, Revision 2, dated March
31, 1994. Accomplishment of such modification constitutes
terminating action for the repetitive inspections required by
paragraphs (g)(1) and (h)(1) of this AD.
(k) New Inspections and Corrective Actions
Except as provided by paragraphs (m)(1) and (m)(2) of this AD:
At the applicable time specified in paragraph 1.E, ``Compliance,''
of Boeing Alert Service Bulletin 737-52A1100, Revision 5, dated
February 14, 2011, do the inspections required by paragraphs (k)(1)
and (k)(2) of this AD, as applicable. Do all applicable related
investigative and corrective actions before further flight, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1100, Revision 5, dated February 14, 2011;
except as required by paragraph (m)(3) of this AD. Accomplishment of
the inspections required by paragraph (k) of this AD terminates the
requirements of the repetitive inspections required by paragraphs
(g)(1) and (h)(1) of this AD. If any cracking is found in the number
4 cross beam, before further flight, repair in accordance with
Boeing Special Attention Service Bulletin 737-52-1149, dated
December 11, 2003.
Note 2 to paragraph (k) of this AD: Boeing Alert Service
Bulletin 737-52A1100, Revision 5, dated February 14, 2011, refers to
Boeing Special Attention Service Bulletin 737-52-1149, dated
December 11, 2003, as an additional source of guidance for the
inspection for cracks of the number 4 cross beam.
(1) For airplanes identified in Tables 1 and 2 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011: Do a one-time HFEC inspection
of the applicable location for cracks, in accordance with the Work
Instructions, Part I, of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011.
(2) For airplanes identified in Table 3 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011: Do a one-time general visual
inspection of the reinforcement angle for excessive shimming or
fastener pull-up, in accordance with the Work Instructions, Part
III, of Boeing Alert Service Bulletin 737-52A1100, Revision 5, dated
February 14, 2011.
(l) No Supplemental Structural Inspections Required by This AD
(1) The supplemental structural inspections specified in Table 4
of paragraph 1.E., ``Compliance,'' and Part 5 of the Accomplishment
Instructions, of Boeing Alert Service Bulletin 737-52A1100, Revision
5, dated February 14, 2011, are not required by this AD.
(2) The supplemental structural inspections specified in Table 4
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1100, Revision 5, dated February 14, 2011, 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)). The corresponding actions specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1100, Revision 5, dated February 14, 2011, are not required by
this AD.
(m) Exceptions to Certain Service Information
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-52A1100, Revision 5, dated February 14, 2011,
specifies a compliance time relative to the Revision 5 issue date of
that service bulletin, this AD requires compliance within the
specified compliance time after the effective date of this AD.
(2) Where Table 1, ``Condition'' column of Paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011, specifies ``airplanes without
either the repair or modification accomplished in accordance with
previous releases of this service bulletin,'' the corresponding
condition in this AD is for ``airplanes on which either a repair or
modification was not accomplished before the effective date of this
AD.''
(3) Where Boeing Alert Service Bulletin 737-52A1100, Revision 5,
dated February 14, 2011, specifies to contact Boeing for certain
actions: Before further flight, do the repair using a method
approved in accordance with the procedures specified in paragraph
(n)(1) of this AD.
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, 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 the
Related Information section of this AD. Information may be emailed
to: 9-ANM-Seattle-ACO-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 required by this AD if it is approved by the
Boeing Commercial Airplanes 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.
(4) AMOCs approved previously in accordance with AD 2000-07-06,
Amendment 39-11660 (65 FR 19302, April 11, 2000), are approved as
AMOCs for the corresponding requirements of this AD.
(o) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone (425)
917-6450; fax (425) 917-6590; email alan.pohl@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
(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.
(3) The following service information was approved for IBR on
June 28, 2013.
(i) Procedure 4, ``Surface Inspection of Aluminum Parts (Meter
Display),'' of Section 51-00-00, of Part 6, ``Eddy Current,'' of
Boeing 737 Nondestructive Test (NDT) Manual, D6-37239, Revision 108,
dated November 15, 2012. The revision level of this document is
identified only in the letter of transmittal; no other page of this
document contains this information.
[[Page 31394]]
(ii) Procedure 23, ``Aluminum Part Surface Inspection (Impedance
Plane Display),'' Section 51-00-00, of Part 6, ``Eddy Current,'' of
Boeing 737 Nondestructive Test (NDT) Manual, D6-37239, Revision 108,
dated November 15, 2012. The revision level of this document is
identified only in the letter of transmittal; no other page of this
document contains this information.
(iii) Boeing Alert Service Bulletin 737-52A1100, Revision 5,
dated February 14, 2011.
(iv) Boeing Special Attention Service Bulletin 737-52-1149,
dated December 11, 2003.
(4) The following service information was approved for IBR on
May 16, 2000 (65 FR 19302, April 11, 2000).
(i) Figure 4, of Section 51-00-00, of Part 6, of Boeing 737
Nondestructive Test (NDT) Manual, D6-37239, dated August 5, 1997.
The revision level is not specified on the title page or list of
effective pages of this document. The title page of this document is
not dated. Pages 1 and 2 of the list of effective pages of this
document are dated August 5, 1997; page 2A is dated February 5,
1997.
(ii) Figure 23, of Section 51-00-00, of Part 6, of Boeing 737
Nondestructive Test (NDT) Manual, D6-37239, dated August 5, 1997.
The revision level is not specified on the title page or list of
effective pages of this document. The title page of this document is
not dated. Pages 1 and 2 of the list of effective pages of this
document are dated August 5, 1997; page 2A is dated February 5,
1997.
(iii) Boeing Service Bulletin 737-52-1100, Revision 2, dated
March 31, 1994.
(5) For Boeing 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.
(6) You may view this service information at FAA, 1601 Lind
Avenue SW., Renton, Washington 98057-3356. For information on the
availability of this material at the FAA, call 425-227-1221.
(7) 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 April 26, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-10797 Filed 5-23-13; 8:45 am]
BILLING CODE 4910-13-P
