Airworthiness Directives; The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 72858-72863 [2011-30603]
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Federal Register / Vol. 76, No. 228 / Monday, November 28, 2011 / Proposed Rules
12,000 total flight cycles or within 1,000
flight cycles after the effective date of this
AD, whichever occurs later, replace the
actuator with a new actuator having P/N
190–70980–405, and modify the attachment
points, in accordance with ‘‘Part I’’ and ‘‘Part
II,’’ as applicable, of the Accomplishment
Instructions of EMBRAER Service Bulletin
190–32–0037, dated October 6, 2010.
(j) For all actuators: Within 20,000 flight
cycles or within 96 months after the effective
date of this AD, whichever occurs first, do
the replacement and modification, as
applicable, in accordance with ‘‘Part III’’ of
EMBRAER Service Bulletin 190–32–0037,
dated October 6, 2010. Doing the actions in
this paragraph is a terminating action for the
requirements specified in paragraphs (g), (h),
and (i) of this AD.
FAA AD Differences
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Note 2: This AD differs from the MCAI
and/or service information as follows:
Brazilian Airworthiness Directive 2011–02–
01, dated February 12, 2011, requires
replacing the MLG retraction actuator, and as
applicable, the anti-rotation pin and
attachment bolt within the next 500 flight
cycles if any discrepancy is found. However,
if any discrepancy is found, this AD requires
replacing the MLG retraction actuator, and as
applicable, the anti-rotation pin and
attachment bolt, before further flight.
Other FAA AD Provisions
(k) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, 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:
Cindy Ashforth, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–2768; fax (425)
227–1149. Information may be emailed to:
9-ANM-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.
(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.
Related Information
(l) Refer to MCAI Brazilian Airworthiness
Directive 2011–02–01, dated February 12,
2011; EMBRAER Service Bulletin 190–32–
0036, dated October 4, 2010; and EMBRAER
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Service Bulletin 190–32–0037, dated October
6, 2010; for related information.
Issued in Renton, Washington, on
November 10, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
and repair if necessary. We are
proposing this AD to detect and correct
fatigue cracking of the intercostals on
the forward and aft sides of the forward
entry door cutout, which could result in
loss of the forward entry door and rapid
decompression of the airplane.
[FR Doc. 2011–30571 Filed 11–25–11; 8:45 am]
DATES:
BILLING CODE 4910–13–P
We must receive comments on
this proposed AD by January 12, 2012.
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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; email
me.boecom@boeing.com; 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.
ADDRESSES:
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1255; Directorate
Identifier 2010–NM–182–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede two
existing airworthiness directives (AD)
that apply to Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. The first existing AD
currently requires, for certain airplanes,
repetitive inspections of the Station
(STA) 348.2 frame to detect cracking
under the stop fittings and intercostal
flanges at stringers S–14L, S–15L, and
S–16L, and corrective action if
necessary. The second existing AD
currently requires repetitive inspections
to detect cracking of the intercostal
webs, attachment clips, and stringer
splice channels, and corrective action if
necessary. Since we issued those ADs,
we have received reports of cracking of
the STA 348.2 frame above the two
outboard fasteners attaching the frame
inner chord and door stop fittings, and
in the outboard chord at stringer S–16L.
We have also received reports of
missing fasteners in the STA 348.2
frame inner chord. This proposed AD
would require additional airplanes to do
the inspection for cracking under the
stop fittings; extend the repetitive
interval for certain airplanes; add a onetime inspection to detect missing
fasteners; and update or add certain
inspection and repair instructions. This
proposed AD would also require, for
certain airplanes, repetitive inspections
of the cargo barrier net fitting for
cracking and repair if necessary. This
proposed AD would also add, for certain
airplanes, repetitive inspections for
cracking of the S–15L aft intercostal,
SUMMARY:
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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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
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:
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Federal Register / Vol. 76, No. 228 / Monday, November 28, 2011 / Proposed Rules
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2011–1255; Directorate Identifier
2010–NM–182–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
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Discussion
On April 20, 2004, we issued AD
2004–09–09, Amendment 39–13598 (69
FR 23646, April 30, 2004), for all Boeing
Model 737–200C series airplanes. That
AD requires repetitive inspections of the
Station (STA) 348.2 frame to detect
cracking under the stop fittings and
intercostal flanges at Stringers S–14L,
S–15L, and S–16L; and corrective action
if necessary. That AD resulted from a
report of cracks in the STA 348.2 frame
on a Boeing Model 737–200C series
airplane. We issued that AD to detect
and correct fatigue cracking of the
intercostals on the forward and aft sides
of the forward entry door cutout, which
could result in the loss of the forward
entry door and rapid decompression of
the airplane.
On July 23, 2009, we issued AD 2009–
16–14, Amendment 39–15987 (74 FR
38901, August 5, 2009), for certain
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
That AD requires repetitive inspections
of the intercostal webs, attachment
clips, and stringer splice channels for
cracks; and corrective action if
necessary. That AD resulted from
reports of fatigue cracks on several
Boeing Model 737–200 series airplanes.
We issued that AD to detect and correct
fatigue cracking of the intercostals on
the forward and aft sides of the forward
entry door, which could result in loss of
the forward entry door and rapid
decompression of the airplane.
Actions Since Existing ADs Were Issued
Since we issued AD 2004–09–09,
Amendment 39–13598 (69 FR 23646,
April 30, 2004), we have received
reports of cracking above the two
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outboard fasteners attaching the frame
inner chord and door stop fitting of the
STA 348.2 frame at S–15L. The cracking
was reported on seven airplanes that
had accumulated between 19,185 and
64,800 flight cycles (AD 2004–09–09
applies only to Model 737–200C
airplanes). Cracking has also been found
in the outboard chord at S–16L. In
addition, we have received reports of 10
airplanes with missing fasteners in the
STA 348.2 frame inner chord at S–7L
through S–15L.
In addition, the requirement to
inspect the intercostal on the aft side at
S–14L to S–16L is common to both AD
2004–09–09, Amendment 39–13598 (69
FR 23646, April 30, 2004), and AD
2009–16–14, Amendment 39–15987 (74
FR 38901, August 5, 2009). Service
history indicates that the repetitive
inspection interval of 6,000 flight cycles
for that area, as required by AD 2009–
16–14, Amendment 39–15987 (74 FR
38901, August 5, 2009), is adequate to
ensure continued operational safety.
The repetitive interval required by AD
2004–09–09, Amendment 39–13598 (69
FR 23646, April 30, 2004), is 4,500 flight
cycles.
Boeing Commercial Airplanes has
received a Organization Designation
Authorization (ODA). We have revised
paragraph (h) of this proposed AD to
delegate the authority to approve an
alternative method of compliance for
any repair required by this AD to the
Boeing Commercial Airplanes ODA
rather than a Designated Engineering
Representative (DER).
Relevant Service Information
We reviewed Boeing Alert Service
Bulletin 737–53A1204, Revision 2,
dated June 24, 2010. The procedures in
Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24,
2010, differ from those in 737–53A1204,
Revision 1, dated March 26, 2007 (the
appropriate source of service
information for AD 2009–16–14 (74 FR
38901, August 5, 2009)), as follows:
• Repetitive detailed and high
frequency eddy current (HFEC)
inspections for cracking of the S–15L aft
intercostal between body station (BS)
348.2 and BS 360 and a detailed
inspection of the cargo barrier net fitting
at the intercostal are added for Model
737–200C airplanes.
• New repair instructions are added
for cracking found at the S–14L, S–15L,
and S–16L intercostals. The repair
includes either doing actions specified
in Boeing Alert Service Bulletin 737–
53A1240, Revision 1, dated June 29,
2010 (described below), or, if a crack is
at the S–15L aft intercostal or the
damage at other intercostal locations is
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outside certain parameters covered in
Boeing Alert Service Bulletin 737–
53A1240, Revision 1, Boeing Alert
Service Bulletin 737–53A1204, Revision
2, dated June 24, 2010, specifies
contacting Boeing for repair
instructions.
We also reviewed Boeing Alert
Service Bulletin 737–53A1240, Revision
1, dated June 29, 2010. The procedures
in Boeing Alert Service Bulletin 737–
53A1240, Revision 1, dated June 29,
2010, differ from those in Boeing Alert
Service Bulletin 737–53A1240, dated
April 10, 2003 (the appropriate source
of service information for AD 2004–09–
09, Amendment 39–13598 (69 FR
23646, April 30, 2004)), as follows:
• All Model 737–100, –200, –300,
–400, and –500 series airplanes (i.e.,
line numbers 1 through 3132) are added
to the effectivity. For these airplanes,
the service bulletin specifies procedures
for inspecting under the stop fitting by
doing HFEC and surface eddy current
inspections for cracking of the frame,
HFEC inspections for cracking of the
reinforcement angle and shear web, and
doing a detailed inspection for cracking
of the STA 348.2 frame outer chord,
inner chord, and reinforcement angle,
and corrective actions if necessary. The
corrective actions include replacing
certain cracked parts with new parts,
and if a crack is found in the frame outer
chord, contacting Boeing for repair
instructions and doing the repair.
• For Model 737–200C airplanes, the
repetitive interval for the HFEC
inspection of the STA 348.2 frame is
extended from 4,500 flight cycles to
6,000 flight cycles.
• For Model 737–100, –200, –300,
–400, and –500 series airplanes, a onetime detailed inspection is added to
detect missing fasteners of the STA
348.2 frame inner chord at S–7L through
S–15L. If any fastener is missing, the
service bulletin specifies to contact
Boeing for repair instructions.
• For all airplanes, intercostal
inspections for cracking between STA
348.2 and STA 360 are now specified in
Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24,
2010. Previously, for the intercostals at
S–14 through S–16L, this inspection
was common to both Boeing Alert
Service Bulletin 737–53A1204 and
Boeing Alert Service Bulletin 737–
53A1240 for Model 737–200C airplanes.
• For Group 3 airplanes, instructions
are added for repair of the STA 348.2
frame inner chord, reinforcement angle,
and shear web; and of the door stop
intercostals at S–14L through S16L.
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Federal Register / Vol. 76, No. 228 / Monday, November 28, 2011 / Proposed Rules
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would retain
certain requirements of AD 2004–09–09,
Amendment 39–13598 (69 FR 23646,
April 30, 2004) and AD 2009–16–14,
Amendment 39–15987 (74 FR 38901,
August 5, 2009). This proposed AD
would add airplanes to the applicability
for the HFEC inspection for cracking of
the stop fittings at the shear web at STA
348.2 frame; extend the repetitive
interval for the HFEC inspection of the
STA 348.2 frame for Model 737–200C
airplanes; add an inspection to detect
missing fasteners of the STA 348.2
frame inner chord; and update or add
certain inspection and repair
instructions. This proposed AD would
also require accomplishing the actions
specified in the service information
described previously.’’
Requirement in AD
2009–16–14, Amendment 39–15987 (74
FR 38901, August 5,
2009)
Corresponding
requirement in this
proposed AD
Changes to Existing ADs
Since those ADs were issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
tables:
paragraph (f)
paragraph (g)
paragraph (h)
paragraph (i)
paragraph (j)
paragraph (k)
paragraph (l)
paragraph (i)
paragraph (j)
paragraph (k)
paragraph (l)
paragraph (m)
paragraph (n)
paragraph (o)
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2004–09–09, Amendment 39–13598 (69
FR 23646, April 30,
2004)
Corresponding
requirement in this
proposed AD
paragraph (a)
paragraph (b)
Costs of Compliance
We estimate that this proposed AD
affects 581 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
paragraph (g)
paragraph (h)
ESTIMATED COSTS
Action
Labor cost
Inspections for cracking under the stop fittings
and intercostal flanges [retained from AD 2004–
09–09, Amendment 39-13598 (69 FR 23646,
April 30, 2004)].
Inspection of areas forward of the aft entry door
[retained from AD 2009–16–14, Amendment
39–15987 (74 FR 38901, August 5, 2009)].
Inspection of areas aft of the forward entry door
[retained from AD 2009–16–14, Amendment
39–15987 (74 FR 38901, August 5, 2009)].
Inspection for missing fasteners [new proposed
action].
18 work-hours × $85 per
hour = $1,530 [per inspection cycle].
$0
$1,530 [per inspection
cycle].
$888,930 [per inspection
cycle].
2 work-hours × $85 per
hour = $170 [per inspection cycle].
1 work-hour × $85 per
hour = $85 [per inspection cycle].
1 work-hour × $85 per
hour = $85.
$0
$170 [per inspection
cycle].
$98,770 [per inspection
cycle].
$0
$85 [per inspection
cycle].
$49,385 [per inspection
cycle].
$561 ...............................
$325,941.
We estimate the following costs to do
any necessary repairs that would be
Parts cost
$476
Cost per product
required based on the results of the
proposed inspections. We have no way
Cost on U.S. operators
of determining the number of aircraft
that might need these repairs:
ON-CONDITION COSTS
Labor cost
Parts cost
Repair of cracking if done in accordance with a method approved by the FAA ..........................
Repair of cracking if done in accordance with Boeing Alert Service Bulletin 737–53A1240 .......
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Action
Unknown .......
24 work-hours
Unknown .......
$11,856 .........
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
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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
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Cost per
product
Unknown.
$13,896.
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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.
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Federal Register / Vol. 76, No. 228 / Monday, November 28, 2011 / Proposed Rules
For the reasons discussed above, I
certify that the proposed regulation:
(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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2004–09–09, Amendment 39–13598 (69
FR 23646, April 30, 2004), and AD
2009–16–14, Amendment 39–15987 (74
FR 38901, August 5, 2009), and adding
the following new AD:
The Boeing Company: Docket No. FAA–
2011–1255; Directorate Identifier 2010–
NM–182–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by January 12, 2012.
Affected ADs
(b) This AD supersedes AD 2004–09–09,
Amendment 39–13598 (69 FR 23646, April
30, 2004); and AD 2009–16–14, Amendment
39–15987 (74 FR 38901, August 5, 2009).
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Applicability
(c) This AD applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
Subject
(d) Joint Aircraft System Component
(JASC)/Air Transport Association (ATA) of
America Code 53, Fuselage.
Unsafe Condition
(e) This AD was prompted by reports of
cracking of the STA 348.2 frame above the
two outboard fasteners attaching the frame
inner chord and door stop fittings, and in the
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outboard chord at stringer S–16L. We have
also received reports of missing fasteners in
the STA 348.2 frame inner chord. We are
issuing this AD to detect and correct fatigue
cracking of the intercostals on the forward
and aft sides of the forward entry door
cutout, which could result in loss of the
forward entry door and rapid decompression
of the airplane.
Compliance
(f) Comply with this AD within the
compliance times specified, unless already
done.
Restatement of the Requirements of AD
2004–09–09, Amendment 39–13598 (69 FR
23646, April 30, 2004) With Revised Service
Information and Extended Repetitive
Intervals
Initial and Repetitive Inspections at STA
348.2 for Model 737–200C Series Airplanes
(g) For Model 737–200C series airplanes:
Except as provided by paragraph (h) of this
AD, prior to the accumulation of 46,000 total
flight cycles, or within 2,250 flight cycles
after June 4, 2004 (the effective date of AD
2004–09–09, Amendment 39–13598 (69 FR
23646, April 30, 2004)), whichever occurs
later, do detailed and eddy current
inspections of the STA 348.2 frame for
cracking under the stop fittings and
intercostal flanges at Stringers 14L, 15L, and
16L by accomplishing paragraphs 3.A. and
3.B.1. through 3.B.7. of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1240, dated April 10, 2003, or by
accomplishing Part 1 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1240, Revision 1, dated June 29,
2010. Do the actions in accordance with
Boeing Alert Service Bulletin 737–53A1240,
dated April 10, 2003; or Revision 1, dated
June 29, 2010. Any applicable repair must be
accomplished prior to further flight. Repeat
the inspections thereafter at intervals not to
exceed 6,000 flight cycles. As of the effective
date of this AD, only Boeing Alert Service
Bulletin 737–53A1240, Revision 1, dated
June 29, 2010, may be used.
Corrective Action for Paragraph (g) of This
AD
(h) If any crack is found during any
inspection required by paragraph (g) of this
AD, and Boeing Alert Service Bulletin 737–
53A1240, dated April 10, 2003; or Revision
1, dated June 29, 2010; specifies to contact
Boeing for appropriate action: Before further
flight, repair in accordance with a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or using a
method approved in accordance with the
procedures specified in paragraph (t) of this
AD.
Restatement of the Requirements of AD
2009–16–14, Amendment 39–15987 (74 FR
38901, August 5, 2009) With Revised Service
Information
Initial Compliance Time
(i) For all Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes, as
identified in Boeing Alert Service Bulletin
737–53A1204, Revision 1, dated March 26,
2007: Before the accumulation of 15,000 total
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flight cycles, or within 4,500 flight cycles
after November 1, 2005 (the effective date of
AD 2005–20–03, Amendment 39–14296 (70
FR 56361, September 27, 2005)), whichever
occurs later: Do the inspections required by
paragraphs (k) and (l) of this AD.
(j) For all Model 737–200C series airplanes,
as identified in Boeing Alert Service Bulletin
737–53A1204, Revision 1, dated March 26,
2007: Before the accumulation of 15,000 total
flight cycles, or within 4,500 flight cycles
after September 9, 2009 (the effective date of
AD 2009–16–14, Amendment 39–15987 (74
FR 38901, August 5, 2009)), whichever
occurs later, do the inspection required by
paragraph (m) of this AD.
Initial Inspection for Group 1 Configuration
Airplanes
(k) For Group 1 airplanes identified in
Boeing Alert Service Bulletin 737–53A1204,
Revision 1, dated March 26, 2007: Perform a
detailed inspection for cracking of the
intercostal web, attachment clips, and
stringer splice channels; and a high
frequency eddy current (HFEC) inspection for
cracking of the stringer splice channels
located forward and aft of the forward entry
door; and do all applicable corrective actions
before further flight; in accordance with Parts
1 and 2 of the Work Instructions of Boeing
Special Attention Service Bulletin 737–53–
1204, dated June 19, 2003; or Boeing Alert
Service Bulletin 737–53A1204, Revision 1,
dated March 26, 2007; or in accordance with
Parts 1, 2, 4, and 5 of the Work Instructions
of Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24, 2010.
After September 9, 2009 and until the
effective date of this AD, Boeing Alert
Service Bulletin 737–53A1204, Revision 1,
dated March 26, 2007; or Revision 2, dated
June 24, 2010; may be used. As of the
effective date of this AD, only Boeing Alert
Service Bulletin 737–53A1204, Revision 2,
dated June 24, 2010, may be used.
Initial Inspection for Cargo Configuration
Airplanes (Forward of the Forward Entry
Door)
(l) For Group 2 cargo airplanes identified
in Boeing Alert Service Bulletin 737–
53A1204, Revision 1, dated March 26, 2007:
Perform a detailed inspection for cracking of
the intercostal webs and attachment clips
located forward of the forward entry door,
and do all applicable corrective actions
before further flight, in accordance with Part
3 of the Work Instructions of Boeing Special
Attention Service Bulletin 737–53–1204,
dated June 19, 2003; or Boeing Alert Service
Bulletin 737–53A1204, Revision 1, dated
March 26, 2007; or in accordance with Part
3 of Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24, 2010.
After September 9, 2009 and until the
effective date of this AD, Boeing Alert
Service Bulletin 737–53A1204, Revision 1,
dated March 26, 2007; or Revision 2, dated
June 24, 2010; may be used. As of the
effective date of this AD, only Boeing Alert
Service Bulletin 737–53A1204, Revision 2,
dated June 24, 2010, may be used.
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Federal Register / Vol. 76, No. 228 / Monday, November 28, 2011 / Proposed Rules
New Requirements of This AD
Initial Inspection for Cargo Configuration
Airplanes (Aft of the Forward Entry Door)
(m) For Group 2 cargo airplanes identified
in Boeing Alert Service Bulletin 737–
53A1204, Revision 1, dated March 26, 2007:
Perform a detailed inspection for cracking of
the intercostal webs and attachment clips
located aft of the forward entry door, and do
all applicable corrective actions before
further flight, in accordance with Part 4 of
the Work Instructions of Boeing Alert Service
Bulletin 737–53A1204, Revision 1, dated
March 26, 2007; or in accordance with Part
3 of Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24, 2010. As
of the effective date of this AD, only Boeing
Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010, may be used.
Repeat Inspections
(n) Repeat the inspections required by
paragraphs (k), (l), and (m) of this AD
thereafter at intervals not to exceed 6,000
flight cycles after the previous inspection, or
within 3,000 flight cycles after September 9,
2009, whichever occurs later.
pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Exceptions to Boeing Special Attention
Service Bulletin 737–53A1204
(o) Do the actions required by paragraphs
(i), (j), (k), (l), (m), and (n) of this AD by
accomplishing all the applicable actions
specified in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–53–1204, dated June 19,
2003; Boeing Alert Service Bulletin 737–
53A1204, Revision 1, dated March 26, 2007;
or Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24, 2010;
except as provided by paragraphs (o)(1) and
(o)(2) of this AD. After September 9, 2009,
and until the effective date of this AD, Boeing
Alert Service Bulletin 737–53A1204,
Revision 1, dated March 26, 2007; or
Revision 2, dated June 24, 2010; may be used.
As of the effective date of this AD, only
Boeing Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010, may be used.
(1) Where Boeing Special Attention Service
Bulletin 737–53–1204, dated June 19, 2003;
Boeing Alert Service Bulletin 737–53A1204,
Revision 1, dated March 26, 2007; or Boeing
Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010; specifies to
contact Boeing for repair instructions: Before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (t) of this AD.
(2) Where Boeing Special Attention Service
Bulletin 737–53–1204, dated June 19, 2003;
or Boeing Alert Service Bulletin 737–
53A1204, Revision 1, dated March 26, 2007;
specifies a compliance time relative to the
date of a service bulletin, this AD requires
compliance relative to September 9, 2009.
Where Boeing Special Attention Service
Bulletin 737–53–1204, dated June 19, 2003;
or Boeing Alert Service Bulletin 737–
53A1204, Revision 1, dated March 26, 2007;
specifies a compliance time relative to the
date of the initial release of the service
bulletin, this AD requires compliance relative
to November 1, 2005 (the effective date of AD
2005–20–03, Amendment 39–14296 (70 FR
56361, September 27, 2005)).
VerDate Mar<15>2010
15:28 Nov 25, 2011
Jkt 226001
One-Time Inspection for Missing Fasteners
at STA 348.2
(p) For Groups 2 and 3 airplanes identified
in Boeing Alert Service Bulletin 737–
53A1240, Revision 1, dated June 29, 2010:
Within 4,500 flight cycles after the effective
date of this AD, do a detailed inspection to
detect missing fasteners of the STA 348.2
frame, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1240, Revision 1,
dated June 29, 2010, except as required by
paragraph (r) of this AD. If any fastener is
missing, before further flight, repair using a
method approved in accordance with the
procedures specified in paragraph (t) of this
AD.
Initial and Repetitive Inspections at STA
348.2 for Model 737–100, –200, –300, –400,
and –500 Series Airplanes
(q) For Groups 2 and 3 airplanes identified
in Boeing Alert Service Bulletin 737–
53A1240, Revision 1, dated June 29, 2010:
Before the accumulation of 15,000 total flight
cycles or within 4,500 flight cycles after the
effective date of this AD, do HFEC and
surface eddy current inspections for cracking
of the frame, HFEC inspections for cracking
of the reinforcement angle and shear web,
and a detailed inspection for cracking of the
STA 348.2 frame outer chord, inner chord,
and reinforcement angle, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1240,
Revision 1, dated June 29, 2010, except as
required by paragraph (r) of this AD. If any
crack is found during any inspection
required by this paragraph, before further
flight, do all applicable corrective actions in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1240, Revision 1, dated June 29,
2010, except as required by paragraph (r) of
this AD, and except where that service
bulletin specifies to contact Boeing, before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (t) of this AD. Repeat
the inspections thereafter at intervals not to
exceed 6,000 flight cycles.
Exception to Boeing Alert Service Bulletin
737–53A1240
(r) Where Boeing Alert Service Bulletin
737–53A1240, Revision 1, dated June 29,
2010, specifies that for the instructions
identified in paragraph 3.B., Work
Instructions, and the Figure(s) which give the
recommended sequence of steps, the
sequence of the steps to do the service
bulletin can be changed; the requirements in
this AD do not allow the sequence of the
steps to be changed.
Initial and Repetitive Inspections of the S–
15L Aft Intercostal and Cargo Barrier Net
Fitting for Model 737–200C Series Airplanes
(s) For Group 2 airplanes identified in
Boeing Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010: Before the
accumulation of 15,000 total flight cycles, or
within 4,500 flight cycles after the effective
date of this AD, whichever occurs later, do
initial detailed and HFEC inspections for
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
cracking of the S–15L aft intercostal between
BS 348.2 and BS 360, and do a detailed
inspection of the cargo barrier net fitting at
the intercostal, in accordance with Figure 3
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010. If any
cracking is found, before further flight repair
using a method approved in accordance with
the procedures specified in paragraph (t) of
this AD. Repeat the inspections at intervals
not to exceed 6,000 flight cycles.
Alternative Methods of Compliance
(AMOCs)
(t)(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, it 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 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.
(4) AMOCs approved for AD 2004–09–09,
Amendment 39–13598 (69 FR 23646, April
30, 2004), are approved as AMOCs for the
corresponding requirements of this AD.
(5) AMOCs approved for AD 2009–16–14,
Amendment 39–15987 (74 FR 38901, August
5, 2009), are approved as AMOCs for the
corresponding requirements of this AD.
Related Information
(u) 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.
(v) 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; email me.boecom@boeing.com; 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.
E:\FR\FM\28NOP1.SGM
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Federal Register / Vol. 76, No. 228 / Monday, November 28, 2011 / Proposed Rules
Issued in Renton, Washington, on
November 18, 2011.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–30603 Filed 11–25–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1250; Directorate
Identifier 2010–NM–031–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 707–100
long body, –200, –100B long body, and
–100B short body series airplanes;
Model 707–300, –300B, –300C, and
–400 series airplanes; and Model 720
and 720B series airplanes. For certain
airplanes, this proposed AD would
require using redefined flight cycle
counts, determining the type of material
of the horizontal stabilizer, rear spar,
upper chords, and lower chords on the
inboard and outboard ends of the rear
spar; repetitively inspecting for cracking
of the horizontal stabilizer components;
and repairing or replacing the chord, or
modification of chord segments made
from 7079 aluminum, if necessary. For
all airplanes, this proposed AD would
require inspecting certain structurally
significant items, and repairing
discrepancies if necessary. This
proposed AD was prompted by reports
of stress corrosion cracking in the chord
segments made from 7079 aluminum in
the horizontal stabilizer rear spar, and
fatigue cracking in the chord segments
made from 7075 aluminum. We are
proposing this AD to detect and correct
stress corrosion and/or fatigue cracking
in the horizontal stabilizer, which could
compromise the structural integrity of
the stabilizer.
DATES: We must receive comments on
this proposed AD by January 12, 2012.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
SUMMARY:
VerDate Mar<15>2010
15:28 Nov 25, 2011
Jkt 226001
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed 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; email
me.boecom@boeing.com; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: (425)
917–6577; fax: (425) 917–6590, email:
berhane.alazar@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2011–1250; Directorate Identifier
2010–NM–031–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
PO 00000
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Fmt 4702
Sfmt 4702
72863
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://www.
regulations.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received numerous reports of
stress corrosion cracking in the chord
segments made from 7079 aluminum in
the Model 707 horizontal stabilizer rear
spar. 7079 aluminum is known to be
susceptible to stress corrosion cracking.
Development of stress corrosion
cracking was slowed by the
accomplishment of the actions specified
in Boeing 707 Service Bulletin 3356,
Revision 2, dated December 12, 1991;
and Boeing 707 Service Bulletin 3381,
Revision 2, dated January 31, 1991.
In addition, we have received three
reports of fatigue cracking in the upper
chords of the horizontal stabilizer rear
spar near the side of the body. These
chords are made from 7075 aluminum.
In all three cases, the actions specified
in Boeing 707/720 Service Bulletin
A3313, Revision 1, dated May 27, 1977,
had been incorporated. The fatigue
cracking in either 7075 or 7079 material
configuration has occurred early in the
life of the modified structure. The
fatigue cracks were generated by
frequent training flights that included
multiple touch-and-go cycles, which are
most prevalent with military operators.
These conditions, if not corrected, could
result in stress corrosion and/or fatigue
cracking in the horizontal stabilizer,
which could compromise the structural
integrity of the stabilizer.
Parts made from 7079 aluminum have
also been discovered on airplanes that
were not originally delivered with those
parts. Therefore, to adequately address
the stress corrosion cracking in the
chord segments in the rear spar of the
horizontal stabilizer, it is necessary to
determine the chord configuration on
the airplane. Furthermore, it is also
necessary to carefully maintain a record
of that configuration until all chord
segments of the rear spar of the
horizontal stabilizers that are made from
7079 aluminum have been removed
from the fleet. Since horizontal
stabilizers can be swapped, it is also
necessary to implement the inspections
for early fatigue cracking on all
airplanes, regardless of their current
usage.
Relevant Service Information
We have reviewed Boeing 707 Alert
Service Bulletin A3515, dated December
E:\FR\FM\28NOP1.SGM
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]]>Agencies
[Federal Register Volume 76, Number 228 (Monday, November 28, 2011)]
[Proposed Rules]
[Pages 72858-72863]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-30603]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1255; Directorate Identifier 2010-NM-182-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 737-100, -200,
-200C, -300, -400, and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede two existing airworthiness directives
(AD) that apply to Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. The first existing AD currently requires, for certain
airplanes, repetitive inspections of the Station (STA) 348.2 frame to
detect cracking under the stop fittings and intercostal flanges at
stringers S-14L, S-15L, and S-16L, and corrective action if necessary.
The second existing AD currently requires repetitive inspections to
detect cracking of the intercostal webs, attachment clips, and stringer
splice channels, and corrective action if necessary. Since we issued
those ADs, we have received reports of cracking of the STA 348.2 frame
above the two outboard fasteners attaching the frame inner chord and
door stop fittings, and in the outboard chord at stringer S-16L. We
have also received reports of missing fasteners in the STA 348.2 frame
inner chord. This proposed AD would require additional airplanes to do
the inspection for cracking under the stop fittings; extend the
repetitive interval for certain airplanes; add a one-time inspection to
detect missing fasteners; and update or add certain inspection and
repair instructions. This proposed AD would also require, for certain
airplanes, repetitive inspections of the cargo barrier net fitting for
cracking and repair if necessary. This proposed AD would also add, for
certain airplanes, repetitive inspections for cracking of the S-15L aft
intercostal, and repair if necessary. We are proposing this AD to
detect and correct fatigue cracking of the intercostals on the forward
and aft sides of the forward entry door cutout, which could result in
loss of the forward entry door and rapid decompression of the airplane.
DATES: We must receive comments on this proposed AD by January 12,
2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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; email me.boecom@boeing.com;
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
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:
[[Page 72859]]
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-1255;
Directorate Identifier 2010-NM-182-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On April 20, 2004, we issued AD 2004-09-09, Amendment 39-13598 (69
FR 23646, April 30, 2004), for all Boeing Model 737-200C series
airplanes. That AD requires repetitive inspections of the Station (STA)
348.2 frame to detect cracking under the stop fittings and intercostal
flanges at Stringers S-14L, S-15L, and S-16L; and corrective action if
necessary. That AD resulted from a report of cracks in the STA 348.2
frame on a Boeing Model 737-200C series airplane. We issued that AD to
detect and correct fatigue cracking of the intercostals on the forward
and aft sides of the forward entry door cutout, which could result in
the loss of the forward entry door and rapid decompression of the
airplane.
On July 23, 2009, we issued AD 2009-16-14, Amendment 39-15987 (74
FR 38901, August 5, 2009), for certain Boeing Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes. That AD requires
repetitive inspections of the intercostal webs, attachment clips, and
stringer splice channels for cracks; and corrective action if
necessary. That AD resulted from reports of fatigue cracks on several
Boeing Model 737-200 series airplanes. We issued that AD to detect and
correct fatigue cracking of the intercostals on the forward and aft
sides of the forward entry door, which could result in loss of the
forward entry door and rapid decompression of the airplane.
Actions Since Existing ADs Were Issued
Since we issued AD 2004-09-09, Amendment 39-13598 (69 FR 23646,
April 30, 2004), we have received reports of cracking above the two
outboard fasteners attaching the frame inner chord and door stop
fitting of the STA 348.2 frame at S-15L. The cracking was reported on
seven airplanes that had accumulated between 19,185 and 64,800 flight
cycles (AD 2004-09-09 applies only to Model 737-200C airplanes).
Cracking has also been found in the outboard chord at S-16L. In
addition, we have received reports of 10 airplanes with missing
fasteners in the STA 348.2 frame inner chord at S-7L through S-15L.
In addition, the requirement to inspect the intercostal on the aft
side at S-14L to S-16L is common to both AD 2004-09-09, Amendment 39-
13598 (69 FR 23646, April 30, 2004), and AD 2009-16-14, Amendment 39-
15987 (74 FR 38901, August 5, 2009). Service history indicates that the
repetitive inspection interval of 6,000 flight cycles for that area, as
required by AD 2009-16-14, Amendment 39-15987 (74 FR 38901, August 5,
2009), is adequate to ensure continued operational safety. The
repetitive interval required by AD 2004-09-09, Amendment 39-13598 (69
FR 23646, April 30, 2004), is 4,500 flight cycles.
Boeing Commercial Airplanes has received a Organization Designation
Authorization (ODA). We have revised paragraph (h) of this proposed AD
to delegate the authority to approve an alternative method of
compliance for any repair required by this AD to the Boeing Commercial
Airplanes ODA rather than a Designated Engineering Representative
(DER).
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 737-53A1204, Revision 2,
dated June 24, 2010. The procedures in Boeing Alert Service Bulletin
737-53A1204, Revision 2, dated June 24, 2010, differ from those in 737-
53A1204, Revision 1, dated March 26, 2007 (the appropriate source of
service information for AD 2009-16-14 (74 FR 38901, August 5, 2009)),
as follows:
Repetitive detailed and high frequency eddy current (HFEC)
inspections for cracking of the S-15L aft intercostal between body
station (BS) 348.2 and BS 360 and a detailed inspection of the cargo
barrier net fitting at the intercostal are added for Model 737-200C
airplanes.
New repair instructions are added for cracking found at
the S-14L, S-15L, and S-16L intercostals. The repair includes either
doing actions specified in Boeing Alert Service Bulletin 737-53A1240,
Revision 1, dated June 29, 2010 (described below), or, if a crack is at
the S-15L aft intercostal or the damage at other intercostal locations
is outside certain parameters covered in Boeing Alert Service Bulletin
737-53A1240, Revision 1, Boeing Alert Service Bulletin 737-53A1204,
Revision 2, dated June 24, 2010, specifies contacting Boeing for repair
instructions.
We also reviewed Boeing Alert Service Bulletin 737-53A1240,
Revision 1, dated June 29, 2010. The procedures in Boeing Alert Service
Bulletin 737-53A1240, Revision 1, dated June 29, 2010, differ from
those in Boeing Alert Service Bulletin 737-53A1240, dated April 10,
2003 (the appropriate source of service information for AD 2004-09-09,
Amendment 39-13598 (69 FR 23646, April 30, 2004)), as follows:
All Model 737-100, -200, -300, -400, and -500 series
airplanes (i.e., line numbers 1 through 3132) are added to the
effectivity. For these airplanes, the service bulletin specifies
procedures for inspecting under the stop fitting by doing HFEC and
surface eddy current inspections for cracking of the frame, HFEC
inspections for cracking of the reinforcement angle and shear web, and
doing a detailed inspection for cracking of the STA 348.2 frame outer
chord, inner chord, and reinforcement angle, and corrective actions if
necessary. The corrective actions include replacing certain cracked
parts with new parts, and if a crack is found in the frame outer chord,
contacting Boeing for repair instructions and doing the repair.
For Model 737-200C airplanes, the repetitive interval for
the HFEC inspection of the STA 348.2 frame is extended from 4,500
flight cycles to 6,000 flight cycles.
For Model 737-100, -200, -300, -400, and -500 series
airplanes, a one-time detailed inspection is added to detect missing
fasteners of the STA 348.2 frame inner chord at S-7L through S-15L. If
any fastener is missing, the service bulletin specifies to contact
Boeing for repair instructions.
For all airplanes, intercostal inspections for cracking
between STA 348.2 and STA 360 are now specified in Boeing Alert Service
Bulletin 737-53A1204, Revision 2, dated June 24, 2010. Previously, for
the intercostals at S-14 through S-16L, this inspection was common to
both Boeing Alert Service Bulletin 737-53A1204 and Boeing Alert Service
Bulletin 737-53A1240 for Model 737-200C airplanes.
For Group 3 airplanes, instructions are added for repair
of the STA 348.2 frame inner chord, reinforcement angle, and shear web;
and of the door stop intercostals at S-14L through S16L.
[[Page 72860]]
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would retain certain requirements of AD 2004-09-
09, Amendment 39-13598 (69 FR 23646, April 30, 2004) and AD 2009-16-14,
Amendment 39-15987 (74 FR 38901, August 5, 2009). This proposed AD
would add airplanes to the applicability for the HFEC inspection for
cracking of the stop fittings at the shear web at STA 348.2 frame;
extend the repetitive interval for the HFEC inspection of the STA 348.2
frame for Model 737-200C airplanes; add an inspection to detect missing
fasteners of the STA 348.2 frame inner chord; and update or add certain
inspection and repair instructions. This proposed AD would also require
accomplishing the actions specified in the service information
described previously.''
Changes to Existing ADs
Since those ADs were issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following tables:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Requirement in AD 2004-09-09,
Amendment 39-13598 (69 FR 23646, Corresponding requirement in this
April 30, 2004) proposed AD
------------------------------------------------------------------------
paragraph (a) paragraph (g)
paragraph (b) paragraph (h)
------------------------------------------------------------------------
------------------------------------------------------------------------
Requirement in AD 2009-16-14,
Amendment 39-15987 (74 FR 38901, Corresponding requirement in this
August 5, 2009) proposed AD
------------------------------------------------------------------------
paragraph (f) paragraph (i)
paragraph (g) paragraph (j)
paragraph (h) paragraph (k)
paragraph (i) paragraph (l)
paragraph (j) paragraph (m)
paragraph (k) paragraph (n)
paragraph (l) paragraph (o)
------------------------------------------------------------------------
Costs of Compliance
We estimate that this proposed AD affects 581 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections for cracking under the 18 work-hours x $85 $0 $1,530 [per $888,930 [per
stop fittings and intercostal per hour = $1,530 inspection cycle]. inspection cycle].
flanges [retained from AD 2004-09- [per inspection
09, Amendment 39[dash]13598 (69 cycle].
FR 23646, April 30, 2004)].
Inspection of areas forward of the 2 work-hours x $85 $0 $170 [per inspection $98,770 [per
aft entry door [retained from AD per hour = $170 [per cycle]. inspection cycle].
2009-16-14, Amendment 39-15987 inspection cycle].
(74 FR 38901, August 5, 2009)].
Inspection of areas aft of the 1 work-hour x $85 per $0 $85 [per inspection $49,385 [per
forward entry door [retained from hour = $85 [per cycle]. inspection cycle].
AD 2009-16-14, Amendment 39-15987 inspection cycle].
(74 FR 38901, August 5, 2009)].
Inspection for missing fasteners 1 work-hour x $85 per $476 $561................ $325,941.
[new proposed action]. hour = $85.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the proposed inspections. We
have no way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair of cracking if done in Unknown................. Unknown................. Unknown.
accordance with a method approved
by the FAA.
Repair of cracking if done in 24 work-hours........... $11,856................. $13,896.
accordance with Boeing Alert
Service Bulletin 737-53A1240.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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.
[[Page 72861]]
For the reasons discussed above, I certify that the proposed
regulation:
(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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 2004-09-09, Amendment 39-13598 (69 FR 23646, April 30, 2004), and
AD 2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2011-1255; Directorate Identifier
2010-NM-182-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by January
12, 2012.
Affected ADs
(b) This AD supersedes AD 2004-09-09, Amendment 39-13598 (69 FR
23646, April 30, 2004); and AD 2009-16-14, Amendment 39-15987 (74 FR
38901, August 5, 2009).
Applicability
(c) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in
any category.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 53, Fuselage.
Unsafe Condition
(e) This AD was prompted by reports of cracking of the STA 348.2
frame above the two outboard fasteners attaching the frame inner
chord and door stop fittings, and in the outboard chord at stringer
S-16L. We have also received reports of missing fasteners in the STA
348.2 frame inner chord. We are issuing this AD to detect and
correct fatigue cracking of the intercostals on the forward and aft
sides of the forward entry door cutout, which could result in loss
of the forward entry door and rapid decompression of the airplane.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Restatement of the Requirements of AD 2004-09-09, Amendment 39-13598
(69 FR 23646, April 30, 2004) With Revised Service Information and
Extended Repetitive Intervals
Initial and Repetitive Inspections at STA 348.2 for Model 737-200C
Series Airplanes
(g) For Model 737-200C series airplanes: Except as provided by
paragraph (h) of this AD, prior to the accumulation of 46,000 total
flight cycles, or within 2,250 flight cycles after June 4, 2004 (the
effective date of AD 2004-09-09, Amendment 39-13598 (69 FR 23646,
April 30, 2004)), whichever occurs later, do detailed and eddy
current inspections of the STA 348.2 frame for cracking under the
stop fittings and intercostal flanges at Stringers 14L, 15L, and 16L
by accomplishing paragraphs 3.A. and 3.B.1. through 3.B.7. of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1240, dated April 10, 2003, or by accomplishing Part 1 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1240, Revision 1, dated June 29, 2010. Do the actions in
accordance with Boeing Alert Service Bulletin 737-53A1240, dated
April 10, 2003; or Revision 1, dated June 29, 2010. Any applicable
repair must be accomplished prior to further flight. Repeat the
inspections thereafter at intervals not to exceed 6,000 flight
cycles. As of the effective date of this AD, only Boeing Alert
Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010, may
be used.
Corrective Action for Paragraph (g) of This AD
(h) If any crack is found during any inspection required by
paragraph (g) of this AD, and Boeing Alert Service Bulletin 737-
53A1240, dated April 10, 2003; or Revision 1, dated June 29, 2010;
specifies to contact Boeing for appropriate action: Before further
flight, repair in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or using a method
approved in accordance with the procedures specified in paragraph
(t) of this AD.
Restatement of the Requirements of AD 2009-16-14, Amendment 39-15987
(74 FR 38901, August 5, 2009) With Revised Service Information
Initial Compliance Time
(i) For all Model 737-100, -200, -200C, -300, -400, and -500
series airplanes, as identified in Boeing Alert Service Bulletin
737-53A1204, Revision 1, dated March 26, 2007: Before the
accumulation of 15,000 total flight cycles, or within 4,500 flight
cycles after November 1, 2005 (the effective date of AD 2005-20-03,
Amendment 39-14296 (70 FR 56361, September 27, 2005)), whichever
occurs later: Do the inspections required by paragraphs (k) and (l)
of this AD.
(j) For all Model 737-200C series airplanes, as identified in
Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March
26, 2007: Before the accumulation of 15,000 total flight cycles, or
within 4,500 flight cycles after September 9, 2009 (the effective
date of AD 2009-16-14, Amendment 39-15987 (74 FR 38901, August 5,
2009)), whichever occurs later, do the inspection required by
paragraph (m) of this AD.
Initial Inspection for Group 1 Configuration Airplanes
(k) For Group 1 airplanes identified in Boeing Alert Service
Bulletin 737-53A1204, Revision 1, dated March 26, 2007: Perform a
detailed inspection for cracking of the intercostal web, attachment
clips, and stringer splice channels; and a high frequency eddy
current (HFEC) inspection for cracking of the stringer splice
channels located forward and aft of the forward entry door; and do
all applicable corrective actions before further flight; in
accordance with Parts 1 and 2 of the Work Instructions of Boeing
Special Attention Service Bulletin 737-53-1204, dated June 19, 2003;
or Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated
March 26, 2007; or in accordance with Parts 1, 2, 4, and 5 of the
Work Instructions of Boeing Alert Service Bulletin 737-53A1204,
Revision 2, dated June 24, 2010. After September 9, 2009 and until
the effective date of this AD, Boeing Alert Service Bulletin 737-
53A1204, Revision 1, dated March 26, 2007; or Revision 2, dated June
24, 2010; may be used. As of the effective date of this AD, only
Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June
24, 2010, may be used.
Initial Inspection for Cargo Configuration Airplanes (Forward of the
Forward Entry Door)
(l) For Group 2 cargo airplanes identified in Boeing Alert
Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007:
Perform a detailed inspection for cracking of the intercostal webs
and attachment clips located forward of the forward entry door, and
do all applicable corrective actions before further flight, in
accordance with Part 3 of the Work Instructions of Boeing Special
Attention Service Bulletin 737-53-1204, dated June 19, 2003; or
Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March
26, 2007; or in accordance with Part 3 of Boeing Alert Service
Bulletin 737-53A1204, Revision 2, dated June 24, 2010. After
September 9, 2009 and until the effective date of this AD, Boeing
Alert Service Bulletin 737-53A1204, Revision 1, dated March 26,
2007; or Revision 2, dated June 24, 2010; may be used. As of the
effective date of this AD, only Boeing Alert Service Bulletin 737-
53A1204, Revision 2, dated June 24, 2010, may be used.
[[Page 72862]]
Initial Inspection for Cargo Configuration Airplanes (Aft of the
Forward Entry Door)
(m) For Group 2 cargo airplanes identified in Boeing Alert
Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007:
Perform a detailed inspection for cracking of the intercostal webs
and attachment clips located aft of the forward entry door, and do
all applicable corrective actions before further flight, in
accordance with Part 4 of the Work Instructions of Boeing Alert
Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or
in accordance with Part 3 of Boeing Alert Service Bulletin 737-
53A1204, Revision 2, dated June 24, 2010. As of the effective date
of this AD, only Boeing Alert Service Bulletin 737-53A1204, Revision
2, dated June 24, 2010, may be used.
Repeat Inspections
(n) Repeat the inspections required by paragraphs (k), (l), and
(m) of this AD thereafter at intervals not to exceed 6,000 flight
cycles after the previous inspection, or within 3,000 flight cycles
after September 9, 2009, whichever occurs later.
Exceptions to Boeing Special Attention Service Bulletin 737-53A1204
(o) Do the actions required by paragraphs (i), (j), (k), (l),
(m), and (n) of this AD by accomplishing all the applicable actions
specified in the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-53-1204, dated June 19, 2003; Boeing
Alert Service Bulletin 737-53A1204, Revision 1, dated March 26,
2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2,
dated June 24, 2010; except as provided by paragraphs (o)(1) and
(o)(2) of this AD. After September 9, 2009, and until the effective
date of this AD, Boeing Alert Service Bulletin 737-53A1204, Revision
1, dated March 26, 2007; or Revision 2, dated June 24, 2010; may be
used. As of the effective date of this AD, only Boeing Alert Service
Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used.
(1) Where Boeing Special Attention Service Bulletin 737-53-1204,
dated June 19, 2003; Boeing Alert Service Bulletin 737-53A1204,
Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin
737-53A1204, Revision 2, dated June 24, 2010; specifies to contact
Boeing for repair instructions: Before further flight, repair using
a method approved in accordance with the procedures specified in
paragraph (t) of this AD.
(2) Where Boeing Special Attention Service Bulletin 737-53-1204,
dated June 19, 2003; or Boeing Alert Service Bulletin 737-53A1204,
Revision 1, dated March 26, 2007; specifies a compliance time
relative to the date of a service bulletin, this AD requires
compliance relative to September 9, 2009. Where Boeing Special
Attention Service Bulletin 737-53-1204, dated June 19, 2003; or
Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March
26, 2007; specifies a compliance time relative to the date of the
initial release of the service bulletin, this AD requires compliance
relative to November 1, 2005 (the effective date of AD 2005-20-03,
Amendment 39-14296 (70 FR 56361, September 27, 2005)).
New Requirements of This AD
One-Time Inspection for Missing Fasteners at STA 348.2
(p) For Groups 2 and 3 airplanes identified in Boeing Alert
Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010:
Within 4,500 flight cycles after the effective date of this AD, do a
detailed inspection to detect missing fasteners of the STA 348.2
frame, in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010,
except as required by paragraph (r) of this AD. If any fastener is
missing, before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (t) of this
AD.
Initial and Repetitive Inspections at STA 348.2 for Model 737-100, -
200, -300, -400, and -500 Series Airplanes
(q) For Groups 2 and 3 airplanes identified in Boeing Alert
Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010:
Before the accumulation of 15,000 total flight cycles or within
4,500 flight cycles after the effective date of this AD, do HFEC and
surface eddy current inspections for cracking of the frame, HFEC
inspections for cracking of the reinforcement angle and shear web,
and a detailed inspection for cracking of the STA 348.2 frame outer
chord, inner chord, and reinforcement angle, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1240, Revision 1, dated June 29, 2010, except as required by
paragraph (r) of this AD. If any crack is found during any
inspection required by this paragraph, before further flight, do all
applicable corrective actions in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1240, Revision
1, dated June 29, 2010, except as required by paragraph (r) of this
AD, and except where that service bulletin specifies to contact
Boeing, before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (t) of this
AD. Repeat the inspections thereafter at intervals not to exceed
6,000 flight cycles.
Exception to Boeing Alert Service Bulletin 737-53A1240
(r) Where Boeing Alert Service Bulletin 737-53A1240, Revision 1,
dated June 29, 2010, specifies that for the instructions identified
in paragraph 3.B., Work Instructions, and the Figure(s) which give
the recommended sequence of steps, the sequence of the steps to do
the service bulletin can be changed; the requirements in this AD do
not allow the sequence of the steps to be changed.
Initial and Repetitive Inspections of the S-15L Aft Intercostal and
Cargo Barrier Net Fitting for Model 737-200C Series Airplanes
(s) For Group 2 airplanes identified in Boeing Alert Service
Bulletin 737-53A1204, Revision 2, dated June 24, 2010: Before the
accumulation of 15,000 total flight cycles, or within 4,500 flight
cycles after the effective date of this AD, whichever occurs later,
do initial detailed and HFEC inspections for cracking of the S-15L
aft intercostal between BS 348.2 and BS 360, and do a detailed
inspection of the cargo barrier net fitting at the intercostal, in
accordance with Figure 3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June
24, 2010. If any cracking is found, before further flight repair
using a method approved in accordance with the procedures specified
in paragraph (t) of this AD. Repeat the inspections at intervals not
to exceed 6,000 flight cycles.
Alternative Methods of Compliance (AMOCs)
(t)(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, it 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 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.
(4) AMOCs approved for AD 2004-09-09, Amendment 39-13598 (69 FR
23646, April 30, 2004), are approved as AMOCs for the corresponding
requirements of this AD.
(5) AMOCs approved for AD 2009-16-14, Amendment 39-15987 (74 FR
38901, August 5, 2009), are approved as AMOCs for the corresponding
requirements of this AD.
Related Information
(u) 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.
(v) 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; email
me.boecom@boeing.com; 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.
[[Page 72863]]
Issued in Renton, Washington, on November 18, 2011.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-30603 Filed 11-25-11; 8:45 am]
BILLING CODE 4910-13-P
