Airworthiness Directives; The Boeing Company Airplanes, 38547-38552 [2012-15601]
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Federal Register / Vol. 77, No. 125 / Thursday, June 28, 2012 / Proposed Rules
PART 1033—MILK IN THE MIDEAST
MARKETING AREA
1. The authority citation for 7 CFR
part 1033 continues to read as follows:
Authority: 7 U.S.C. 601–674, and 7253.
2. Amend § 1033.7 by revising
paragraph (a) to read as follows:
§ 1033.7
Pool Plant
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(a) A distributing plant, other than a
plant qualified as a pool plant pursuant
to paragraph (b) of this section or
§ ___.7(b) of any other Federal milk
order, from which during the month 30
percent or more of the total quantity of
fluid milk products physically received
at the plant (excluding concentrated
milk received from another plant by
agreement for other than class I use) are
disposed of as route disposition or are
transferred in the form of packaged fluid
milk products to other distributing
plants. At least 25 percent of such route
disposition and transfers must be to
outlets in the marketing area. Plants
located within the marketing area that
meet the 30 percent route disposition
standard contained above, and have
combined route disposition and
transfers of at least 50 percent into
Federal order marketing areas will be
regulated as a distributing plant in this
order.
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Dated: June 22, 2012.
David R. Shipman,
Administrator, Agricultural Marketing
Service.
[FR Doc. 2012–15670 Filed 6–27–12; 8:45 am]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0645; Directorate
Identifier 2011–NM–052–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
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AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to all The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. The
existing AD currently requires repetitive
SUMMARY:
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inspections to detect cracking in the
web of the aft pressure bulkhead at body
station 1016 at the aft fastener row
attachment to the ‘‘Y’’ chord, and
corrective actions if necessary. That AD
was prompted by several reports of
fatigue cracking at that location, which
could result in rapid decompression of
the fuselage. Since we issued that AD,
we have received additional reports of
cracks found in the aft pressure
bulkhead. This proposed AD would add
various inspections for discrepancies at
the aft pressure bulkhead, and related
investigative and corrective actions if
necessary. We are proposing this AD to
detect and correct such fatigue cracking,
which could result in rapid
decompression of the fuselage.
DATES: We must receive comments on
this proposed AD by August 13, 2012.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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 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; 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.
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38547
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:
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–2012–0645; Directorate Identifier
2011–NM–052–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 9, 1999, we issued AD 99–
08–23, Amendment 39–11132 (64 FR
19879, April 23, 1999), for all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. That AD requires repetitive
inspections of the web of the aft
pressure bulkhead at body station 1016
at the aft fastener row attachment to the
‘‘Y’’ chord; and corrective actions, if
necessary. That AD resulted from
reports of fatigue cracking found at that
location on The Boeing Company Model
737 series airplanes. We issued that AD
to detect and correct such fatigue
cracking, which could result in rapid
decompression of the fuselage.
Actions Since Existing AD Was Issued
Since we issued AD 99–08–23,
Amendment 39–11132 (64 FR 19879,
April 23, 1999), we have received
reports that cracks have been found in
four general areas of the aft pressure
bulkhead: In the web at the web-to-‘‘Y’’
chord interface, in the web at the outer
circumferential tear strap, in the web
near the dome cap, and in the ‘‘Z’’
stiffeners near the dome cap. Cracks
have been reported in these new areas
on airplanes that have accumulated
between 21,246 and 68,000 total flight
cycles, and between 17,500 and 61,000
total flight hours.
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Relevant Service Information
We reviewed Boeing Alert Service
Bulletin 737–53A1214, Revision 4,
dated December 16, 2011. The service
information describes procedures and
compliance times for various
inspections for discrepancies (including
cracking, misdrilled fastener holes,
elongated fastener holes, corrosion, oilcans, and existing repairs) at the aft
pressure bulkhead, and related
investigative and corrective actions if
necessary, as follows:
• Repetitive detailed and low
frequency eddy current (LFEC)
inspections of the aft side of the upper
bulkhead web, or detailed and high
frequency eddy current (HFEC)
inspections from the forward side of the
bulkhead, to detect cracks, incorrectly
drilled fastener holes, or elongated
fastener holes; and related investigative
actions, including HFEC and detailed
inspections to detect additional cracks,
incorrectly drilled fastener holes, or
elongated fastener holes on the section
of the web of the forward side of the
bulkhead.
• Repetitive detailed, surface HFEC,
and subsurface LFEC inspections to
detect cracks, incorrectly drilled
fastener holes, or elongated fastener
holes of the lower bulkhead web from
the forward or aft side of the bulkhead.
• A one-time LFEC inspection to
detect cracks on the aft side of the
bulkhead of the web located under the
outer circumferential tear strap, or a
one-time HFEC inspection to detect
cracks from the forward side of the
bulkhead of the web located under the
outer circumferential tear strap.
• A detailed inspection from the aft
side of the bulkhead for oil-canning, and
related investigative actions. The related
investigative actions include detailed
and HFEC inspections for cracks, and a
measurement of the depth and width of
the oil-can. For airplanes on which oilcans are found within limits, the service
information specifies an option of doing
repetitive detailed and HFEC
inspections for cracks of the oil-canning
and eventual repair. Doing the repair
terminates the repetitive inspections.
• Repetitive eddy current inspections
to detect cracks of the dome cap at the
center of the bulkhead.
• Repetitive HFEC inspections to
detect cracks of the ‘‘Z’’ stiffener flanges
at the dome cap in the center of the
bulkhead.
• A detailed inspection of the
bulkhead web and of the stiffeners for
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existing repairs; and, depending on the
findings, repetitive HFEC or LFEC
inspections of the web for cracking;
replacement of existing repairs with
new repairs, and damage tolerance
inspections.
• The corrective actions include
repairing discrepancies (including
cracking, misdrilled fastener holes,
elongated fastener holes, corrosion, oilcans, and existing repairs), or for certain
discrepancies, contacting Boeing for
repair instructions.
• The initial compliance times vary
depending on inspection type and area.
The earliest initial inspection is within
375 flight cycles after the effective date
of this AD. The latest initial inspection
is within 6,000 flight cycles or 24
months after the effective date of this
AD, whichever occurs first.
The compliance times for the option,
for airplanes on which oil-cans are
found within limits, of doing repetitive
detailed and HFEC inspections for
cracks of the oil-canning and eventual
repair are as follows: The initial
inspections are done before further
flight. The repetitive interval is 1,200
flight cycles. The repair must be done
within 12,000 flight cycles after the oilcan was found.
The repetitive inspections range from
intervals not to exceed 6,000 flight
cycles to intervals not to exceed 12,000
flight cycles, depending on the
inspection type and area.
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 all
requirements of AD 99–08–23,
Amendment 39–11132 (64 FR 19879,
April 23, 1999). This proposed AD
would also require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Differences
Between the Proposed AD and the
Service Information.’’
Changes to Existing AD
This proposed AD would retain all
requirements of AD 99–08–23,
Amendment 39–11132 (64 FR 19879,
April 23, 1999). Since AD 99–08–23 was
issued, the AD format has been revised,
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and certain paragraphs have been
rearranged. As a result, the
corresponding paragraph identifiers
have changed in this proposed AD, as
listed in the following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
99–08–23, Amendment 39–11132 (64
FR 19879, April 23,
1999)
paragraph
paragraph
paragraph
paragraph
(a)
(b)
(c)
(d)
Corresponding
requirement in this
proposed AD
paragraph
paragraph
paragraph
paragraph
(g)
(h)
(i)
(j)
Boeing Commercial Airplanes has
received an Organization Designation
Authorization (ODA). We have revised
this proposed AD to delegate the
authority to approve an alternative
method of compliance for any repair
required by this proposed AD to the
Boeing Commercial Airplanes ODA
rather than a Designated Engineering
Representative (DER).
We have revised the date of the
document specified in paragraph (j)(1)
of this proposed AD (which is a
restatement of paragraph (d)(1) of AD
99–08–23, Amendment 39–11132 (64
FR 19879, April 23, 1999)), to November
5, 1995, as specified in the
‘‘Incorporation of Reference’’ paragraph
of AD 99–08–23 (paragraph (g) of AD
99–08–23).
Differences Between the Proposed AD
and the Service Information
Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December
16, 2011, specifies to contact the
manufacturer for instructions on how to
repair certain conditions, but this
proposed AD would require repairing
those conditions in one of the following
ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) whom
we have authorized to make those
findings.
Costs of Compliance
We estimate that this proposed AD
affects 566 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
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ESTIMATED COSTS
Action
Labor cost
LFEC [retained actions from AD 99–08–23,
Amendment 39–11132 (64 FR 19879, April
23, 1999)].
Detailed visual inspection [retained actions from
AD 99–08-23, Amendment 39–11132 (64 FR
19879, April 23, 1999)].
Detailed, HFEC, and LFEC inspections of the
web at the ‘‘Y’’ chord of the bulkhead, the web
located under the outer circumferential tear
strap, the ‘‘Z’’ stiffeners at the dome cap, and
existing repairs [new proposed action].
8 work-hours × $85 per
hour = $680.
$0
$680 .............................
$384,880.
2 work-hours × $85 per
hour = $170.
0
$170 .............................
$96,220.
Up to 60 work-hours ×
$85 per hour =
$5,100 per inspection
cycle.
0
$5,100 per inspection
cycle.
$2,886,600 per inspection cycle.
We estimate the following costs to do
any necessary on-condition inspections
that would be required based on the
Parts cost
Cost per product
results of the proposed initial
inspection. We have no way of
Cost on U.S. operators
determining the number of aircraft that
might need these inspections:
ON-CONDITION COSTS
Action
Labor cost
Detailed and HFEC inspections for oil-canning ...........
LFEC or HFEC inspections for cracking ......................
1 work-hour × $85 per hour = $85 ...............................
2 work-hours × $85 per hour = $170 ...........................
We have received no definitive data
that would enable us to provide cost
estimates for the crack repairs specified
in this proposed 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.
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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
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responsibilities among the various
levels of government.
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)
99–08–23, Amendment 39–11132 (64
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Cost per
product
Parts cost
$0
0
$85
170
FR 19879, April 23, 1999), and adding
the following new AD:
The Boeing Company: Docket No. FAA–
2012–0645; Directorate Identifier 2011–
NM–052–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by August 13, 2012.
(b) Affected ADs
This AD supersedes AD 99–08–23,
Amendment 39–11132 (64 FR 19879, April
23, 1999).
(c) Applicability
This AD applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes;
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by several reports
of fatigue cracks in the aft pressure bulkhead.
We are issuing this AD to detect and correct
such fatigue cracking, which could result in
rapid decompression of the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Initial Inspection
This paragraph restates the initial
inspection required by paragraph (a) of AD
99–08–23, Amendment 39–11132 (64 FR
19879, April 23, 1999). Perform either
inspection specified by paragraph (g)(1) or
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(g)(2) of this AD at the time specified in
paragraph (h) of this AD.
(1) Perform a low frequency eddy current
(LFEC) inspection from the aft side of the aft
pressure bulkhead to detect discrepancies
(including cracking, misdrilled fastener
holes, and corrosion) of the web of the upper
section of the aft pressure bulkhead at body
station 1016 at the aft fastener row
attachment to the ‘‘Y’’ chord, from stringer 15
left to stringer 15 right, in accordance with
Boeing 737 Nondestructive Test Manual D6–
37239, Part 6, Section 53–10–54, dated
December 5, 1998.
(2) Perform a detailed visual inspection of
the aft fastener row attachment to the ‘‘Y’’
chord from the forward side of the aft
pressure bulkhead to detect discrepancies
(including cracking, misdrilled fastener
holes, and corrosion) of the entire web of the
aft pressure bulkhead at body station 1016.
(h) Retained Compliance Times
This paragraph restates the compliance
times specified in paragraph (b) of AD 99–
08–23, Amendment 39–11132 (64 FR 19879,
April 23, 1999). Perform the inspection
required by paragraph (g) of this AD at the
time specified in paragraph (h)(1), (h)(2), or
(h)(3) of this AD, as applicable.
(1) For airplanes that have accumulated
40,000 or more total flight cycles as of May
10, 1999 (the effective date of AD 99–08–23,
Amendment 39–11132 (64 FR 19879, April
23, 1999)): Inspect within 375 flight cycles or
60 days after May 10, 1999, whichever occurs
later.
(2) For airplanes that have accumulated
25,000 or more total flight cycles and fewer
than 40,000 total flight cycles as of May 10,
1999 (the effective date of AD 99–08–23,
Amendment 39–11132 (64 FR 19879, April
23, 1999)): Inspect within 750 flight cycles or
90 days after May 10, 1999, whichever occurs
later.
(3) For airplanes that have accumulated
fewer than 25,000 total flight cycles as of
May 10, 1999 (the effective date of AD 99–
08–23, Amendment 39–11132 (64 FR 19879,
April 23, 1999)): Inspect prior to the
accumulation of 25,750 total flight cycles.
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(i) Retained Repetitive Inspections
This paragraph restates the repetitive
inspections required by paragraph (c) of AD
99–08–23, Amendment 39–11132 (64 FR
19879, April 23, 1999). Within 1,200 flight
cycles after performing the initial inspection
required by paragraph (g) of this AD, and
thereafter at intervals not to exceed 1,200
flight cycles: Perform either inspection
specified by paragraph (g)(1) or (g)(2) of this
AD.
(j) Retained Corrective Actions
This paragraph restates the corrective
actions required by paragraph (d) of AD 99–
08–23, Amendment 39–11132 (64 FR 19879,
April 23, 1999). If any discrepancy is
detected during any inspection required by
paragraph (g), (h), or (i) of this AD: Prior to
further flight, accomplish the actions
specified by paragraphs (j)(1) and (j)(3) of this
AD, and paragraph (j)(2) of this AD, if
applicable.
(1) Perform a high frequency eddy current
inspection from the forward side of the
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bulkhead to detect cracking of the web at the
‘‘Y’’ chord attachment, around the entire
periphery of the ‘‘Y’’ chord, in accordance
with Boeing 737 Nondestructive Test Manual
D6–37239, Part 6, Section 51–00–00, Figure
23, dated November 5, 1995.
(2) If the most recent inspection performed
in accordance with paragraph (g) of this AD
was not a detailed visual inspection:
Accomplish the actions specified by
paragraph (g)(2) of this AD. If the inspection
was a detailed visual inspection, it is not
necessary to repeat that inspection prior to
further flight.
(3) Repair any discrepancy such as
cracking or corrosion or misdrilled fastener
holes using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(k) New Requirements: Inspections of the
Web at the ‘‘Y’’ Chord Upper Bulkhead From
S–15L to S–15R
At the later of the times specified in
paragraphs (k)(1) and (k)(2) of this AD: Do
detailed and LFEC inspections of the aft side
of the bulkhead web, or do detailed and
HFEC inspections from the forward side of
the bulkhead, and do all applicable related
investigative and corrective actions; in
accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011, except as required
by paragraphs (r)(1) and (r)(3) of this AD.
Inspect for cracks, incorrectly drilled fastener
holes, and elongated fastener holes. Do all
applicable related investigative and
corrective actions before further flight.
Repeat the inspections at the applicable
times specified in table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011.
(1) Prior to the accumulation of 25,000
total flight cycles.
(2) Except as required by paragraphs (r)(2)
and (r)(4) of this AD, at the later of the times
specified in the ‘‘Compliance Time’’ column
in table 1 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December 16,
2011.
(l) New Requirements: Inspections of the
Web at the ‘‘Y’’ Chord in the Lower
Bulkhead From S–15L to S–15R
Except as required by paragraphs (r)(2) and
(r)(5) of this AD, at the applicable time
specified in table 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Do detailed and eddy
current inspections of the web from the
forward or aft side of the bulkhead for cracks,
incorrectly drilled fasteners, and elongated
fasteners, in accordance with Part III of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011, except as required
by paragraphs (r)(1) and (r)(3) of this AD. If
any crack, incorrectly drilled fastener,
elongated fastener, or corrosion is found,
before further flight, repair the web using a
method approved in accordance with the
procedures specified in paragraph (u) of this
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AD. Repeat the inspections at the applicable
times specified in table 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011.
(m) New Requirements: One-Time Inspection
Under the Tear Strap
Except as required by paragraphs (r)(2) and
(r)(5) of this AD, at the applicable time
specified in table 3 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Do a one-time LFEC
inspection for cracks on the aft side of the
bulkhead of the web located under the outer
circumferential tear strap, or do a one-time
HFEC inspection for cracks from the forward
side of the bulkhead of the web located under
the outer circumferential tear strap, in
accordance with Part II of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011, except as required
by paragraph (r)(1) of this AD. If any cracking
is found, before further flight, repair the
bulkhead using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(n) New Requirements: Inspection for OilCanning
Except as required by paragraph (r)(2) of
this AD, at the applicable time specified in
table 4 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011: Do a
detailed inspection from the aft side of the
bulkhead for oil-canning and do all
applicable related investigative and
corrective actions, in accordance with Part II
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, except
as required by paragraph (r)(1) of this AD. Do
all related investigative and corrective
actions before further flight. Thereafter,
repeat the inspection at the applicable times
specified in table 4 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011. For oil-cans found
within the limits specified in Part II of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011: In lieu of installing
the repair before further flight, at the
applicable times specified in table 4 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, do
initial and repetitive detailed and HFEC
inspections for cracks of the oil-canning and
install the repair, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011. If any crack is
found, before further flight, repair the
cracking using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD. Installing the repair
terminates the repetitive inspections for
cracks.
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Federal Register / Vol. 77, No. 125 / Thursday, June 28, 2012 / Proposed Rules
(o) New Requirements: Inspection of the
Dome Cap at the Center of the Bulkhead
Except as required by paragraphs (r)(2) and
(r)(5) of this AD, at the applicable time
specified in table 5 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Do an eddy current
inspection to detect any cracking of the dome
cap at the center of the bulkhead, and do all
applicable corrective actions, in accordance
with Part IV of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011. Do all corrective actions before
further flight. Repeat the inspection at the
times specified in table 5 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011.
rmajette on DSK2TPTVN1PROD with PROPOSALS
(p) New Requirements: Inspection of the
Forward Flange of the ‘‘Z’’ Stiffeners at the
Dome Cap
Except as required by paragraphs (r)(2) and
(r)(5) of this AD, at the applicable time
specified in table 6 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Do an HFEC inspection
to detect any cracking of the ‘‘Z’’ stiffener
flanges at the dome cap in the center of the
bulkhead, in accordance with Part V of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011, except as required
by paragraph (r)(1) of this AD. If any crack
is found, before further flight, repair the
flanges using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD. Repeat the
inspection at the applicable times specified
in table 6 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December 16,
2011.
(q) New Requirement: Inspection for Existing
Repairs on the Bulkhead
Except as required by paragraph (r)(2) of
this AD, at the applicable time specified in
table 7 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011: Do a
detailed inspection of the bulkhead web and
stiffeners for existing repairs, in accordance
with Part VI of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, except as required by paragraph
(r)(1) of this AD.
(1) If any repair identified in the
‘‘Condition’’ column of table 8 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, is found and the
‘‘Reference’’ column refers to Appendix A, B,
C, or D of that service bulletin: At the
applicable times specified in table 8 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, except
as required by paragraph (r)(2) of this AD, do
a HFEC inspection or a LFEC inspection of
the web for cracking, in accordance with
Appendix A, B, C, or D, as applicable, of
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Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011. If any
cracking is found, before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (u) of
this AD. Repeat the inspections, thereafter, at
the applicable intervals specified in table 8
of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011.
(2) If any repair identified in the
‘‘Condition’’ column of table 8 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, is found and the
‘‘Reference’’ column refers to Appendix E of
that service bulletin: At the applicable times
specified in table 8 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, except as required by
paragraph (r)(2) of this AD, remove the repair
and replace with a new repair, in accordance
with Appendix E of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011.
(3) If any non-SRM (structural repair
manual) repair is found and the repair does
not have FAA-approved damage tolerance
inspections, except as required by paragraph
(r)(2) of this AD, at the applicable time
specified in table 7 of Paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Contact the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, for damage tolerance inspections. Do
those damage tolerance inspections at the
times given using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(r) Exceptions to the Service Bulletin
(1) Where Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, specifies to contact Boeing for
repair instructions: Before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(2) Where Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, specifies a compliance time ‘‘after
the date of Revision 1 to this service
bulletin,’’ ‘‘from the date of Revision 3 of this
service bulletin,’’ ‘‘after the date of Revision
3 to this service bulletin,’’ or ‘‘of the effective
date of AD 99–08–23,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(3) Access and restoration procedures
specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, are not required by this AD.
Operators may do those procedures following
their maintenance practices.
(4) Where table 1 of paragraph 1.E.,
‘‘Compliance’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, specifies a compliance
time relative to actions done ‘‘in accordance
with paragraph (a)(2) of AD 99–08–23,’’ this
AD requires compliance within the specified
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
38551
compliance time relative to actions specified
in paragraph (g)(2) of this AD.
(5) Where the Condition columns in tables
2, 3, 5, and 6 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, refer to total flight cycles,
this AD applies to the airplanes with the
specified total flight cycles as of the effective
date of this AD.
(s) Terminating Action
Accomplishment of the requirements of
paragraphs (k) through (q) of this AD
terminates the requirements of paragraphs (g)
through (j) of this AD.
(t) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (k) through (s)
of this AD, if the actions were performed
before the effective date of this AD using the
service bulletins specified in paragraphs
(t)(1) through (t)(4) of this AD.
(1) Boeing Alert Service Bulletin 737–
53A1214, dated June 17, 1999.
(2) Boeing Alert Service Bulletin 737–
53A1214, Revision 1, dated June 22, 2000.
(3) Boeing Alert Service Bulletin 737–
53A1214, Revision 2, dated May 24, 2001.
(4) Boeing Alert Service Bulletin 737–
53A1214, Revision 3, dated January 19, 2011.
(u) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in 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 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 previously in
accordance with AD 99–08–23, Amendment
39–11132 (64 FR 19879, April 23, 1999), are
approved as AMOCs for the corresponding
provisions of this AD.
(v) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; phone: (425) 917–6440; fax: (425) 917–
6590; email: alan.pohl@faa.gov.
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38552
Federal Register / Vol. 77, No. 125 / Thursday, June 28, 2012 / Proposed Rules
(2) 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; 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.
Issued in Renton, Washington, on June 18,
2012.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–15601 Filed 6–27–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
Docket No. FAA–2011–1181; Airspace
Docket No. 11–ANM–20
Proposed Amendment of Class E
Airspace; Boise, ID
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM).
AGENCY:
The FAA is issuing a SNPRM
for the notice of proposed rulemaking
(NPRM) published on February 7, 2012,
in order to elicit comments regarding
removing reference to the navigation aid
in the legal description of the Class E
airspace area designated as an extension
at Boise Air Terminal (Gowen Field),
Boise, ID. The NPRM only proposed an
amendment of Class E airspace
extending upward from 700 feet above
the surface at the airport, as well as
adjusting the geographic coordinates of
the airport. The FAA is proposing this
amendment to enhance safety in the
Boise, ID, airspace area.
DATES: Comments must be received on
or before August 13, 2012.
ADDRESSES: Send comments on this
proposal 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;
telephone (202) 366–9826. You must
identify FAA Docket No. FAA–2011–
1181; Airspace Docket No. 11–ANM–20,
at the beginning of your comments. You
may also submit comments through the
Internet at https://www.regulations.gov.
rmajette on DSK2TPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
15:17 Jun 27, 2012
Jkt 226001
FOR FURTHER INFORMATION CONTACT:
Eldon Taylor, Federal Aviation
Administration, Operations Support
Group, Western Service Center, 1601
Lind Avenue SW., Renton, WA 98057;
telephone (425) 203–4537.
SUPPLEMENTARY INFORMATION:
History
On February 7, 2012, the FAA
published a NPRM to amend Class E
airspace, extending upward from 700
feet or more above the surface, at Boise
Air Terminal (Gowen Field), Boise, ID,
UT (77 FR 6026). The comment period
closed March 23, 2012. No comments
were received. Subsequent to
publication, it was discovered by
National Aeronautical Navigation
Services (NANS) that the legal
description for the Boise, ID, Class E
airspace area designated as an extension
needed editing to better describe the
airspace. The FAA seeks comments on
this SNPRM.
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers (FAA Docket No. FAA
2011–1181 and Airspace Docket No. 11–
ANM–20) and be submitted in triplicate
to the Docket Management System (see
ADDRESSES section for address and
phone number). You may also submit
comments through the Internet at
https://www.regulations.gov.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this action must submit with those
comments a self-addressed stamped
postcard on which the following
statement is made: ‘‘Comments to FAA
Docket No. FAA–2011–1181 and
Airspace Docket No. 11–ANM–20.’’ The
postcard will be date/time stamped and
returned to the commenter.
All communications received on or
before the specified closing date for
comments will be considered before
taking action on the proposed rule. The
proposal contained in this action may
be changed in light of comments
received. All comments submitted will
be available for examination in the
public docket both before and after the
closing date for comments. A report
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Fmt 4702
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summarizing each substantive public
contact with FAA personnel concerned
with this rulemaking will be filed in the
docket.
Availability of NPRMs
An electronic copy of this document
may be downloaded through the
Internet at https://www.regulations.gov.
Recently published rulemaking
documents can also be accessed through
the FAA’s Web page at https://
www.faa.gov/airports_airtraffic/air_
traffic/publications/airspace_
amendments/.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office (see the
ADDRESSES section for the address and
phone number) between 9:00 a.m. and
5:00 p.m., Monday through Friday,
except federal holidays. An informal
docket may also be examined during
normal business hours at the Northwest
Mountain Regional Office of the Federal
Aviation Administration, Air Traffic
Organization, Western Service Center,
Operations Support Group, 1601 Lind
Avenue SW., Renton, WA 98057.
Persons interested in being placed on
a mailing list for future NPRMs should
contact the FAA’s Office of Rulemaking,
(202) 267–9677, for a copy of Advisory
Circular No. 11–2A, Notice of Proposed
Rulemaking Distribution System, which
describes the application procedure.
The Supplemental Proposal
The FAA is proposing an amendment
to Title 14 Code of Federal Regulations
(14 CFR) part 71 by amending the Class
E airspace area designated as an
extension, at Boise Air Terminal
(Gowen Field), Boise, ID. The legal
description would be rewritten to better
describe the airspace area by removing
reference to the Boise VHF–OmniDirectional Radio Range Tactical Air
Navigational Aid (VORTAC). Class E
airspace extending upward from 700
feet above the surface would be
reconfigured due to the
decommissioning of the Donnelly
Tactical Air Navigational Aid (TACAN).
The geographic coordinates of the
airport would be adjusted in accordance
with the FAA’s aeronautical database.
This action would enhance the safety
and management of IFR operations at
the airport.
Class E airspace designations are
published in paragraph 6003 and 6005,
respectively, of FAA Order 7400.9V,
dated August 9, 2011, and effective
September 15, 2011, which is
incorporated by reference in 14 CFR
part 71.1. The Class E airspace
designation listed in this document will
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]]>Agencies
[Federal Register Volume 77, Number 125 (Thursday, June 28, 2012)]
[Proposed Rules]
[Pages 38547-38552]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-15601]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0645; Directorate Identifier 2011-NM-052-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to all The Boeing Company Model 737-100, -200, -200C,
-300, -400, and -500 series airplanes. The existing AD currently
requires repetitive inspections to detect cracking in the web of the
aft pressure bulkhead at body station 1016 at the aft fastener row
attachment to the ``Y'' chord, and corrective actions if necessary.
That AD was prompted by several reports of fatigue cracking at that
location, which could result in rapid decompression of the fuselage.
Since we issued that AD, we have received additional reports of cracks
found in the aft pressure bulkhead. This proposed AD would add various
inspections for discrepancies at the aft pressure bulkhead, and related
investigative and corrective actions if necessary. We are proposing
this AD to detect and correct such fatigue cracking, which could result
in rapid decompression of the fuselage.
DATES: We must receive comments on this proposed AD by August 13, 2012.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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 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; 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:
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-2012-0645;
Directorate Identifier 2011-NM-052-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 9, 1999, we issued AD 99-08-23, Amendment 39-11132 (64 FR
19879, April 23, 1999), for all The Boeing Company Model 737-100, -200,
-200C, -300, -400, and -500 series airplanes. That AD requires
repetitive inspections of the web of the aft pressure bulkhead at body
station 1016 at the aft fastener row attachment to the ``Y'' chord; and
corrective actions, if necessary. That AD resulted from reports of
fatigue cracking found at that location on The Boeing Company Model 737
series airplanes. We issued that AD to detect and correct such fatigue
cracking, which could result in rapid decompression of the fuselage.
Actions Since Existing AD Was Issued
Since we issued AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999), we have received reports that cracks have been found in four
general areas of the aft pressure bulkhead: In the web at the web-to-
``Y'' chord interface, in the web at the outer circumferential tear
strap, in the web near the dome cap, and in the ``Z'' stiffeners near
the dome cap. Cracks have been reported in these new areas on airplanes
that have accumulated between 21,246 and 68,000 total flight cycles,
and between 17,500 and 61,000 total flight hours.
[[Page 38548]]
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 737-53A1214, Revision 4,
dated December 16, 2011. The service information describes procedures
and compliance times for various inspections for discrepancies
(including cracking, misdrilled fastener holes, elongated fastener
holes, corrosion, oil-cans, and existing repairs) at the aft pressure
bulkhead, and related investigative and corrective actions if
necessary, as follows:
Repetitive detailed and low frequency eddy current (LFEC)
inspections of the aft side of the upper bulkhead web, or detailed and
high frequency eddy current (HFEC) inspections from the forward side of
the bulkhead, to detect cracks, incorrectly drilled fastener holes, or
elongated fastener holes; and related investigative actions, including
HFEC and detailed inspections to detect additional cracks, incorrectly
drilled fastener holes, or elongated fastener holes on the section of
the web of the forward side of the bulkhead.
Repetitive detailed, surface HFEC, and subsurface LFEC
inspections to detect cracks, incorrectly drilled fastener holes, or
elongated fastener holes of the lower bulkhead web from the forward or
aft side of the bulkhead.
A one-time LFEC inspection to detect cracks on the aft
side of the bulkhead of the web located under the outer circumferential
tear strap, or a one-time HFEC inspection to detect cracks from the
forward side of the bulkhead of the web located under the outer
circumferential tear strap.
A detailed inspection from the aft side of the bulkhead
for oil-canning, and related investigative actions. The related
investigative actions include detailed and HFEC inspections for cracks,
and a measurement of the depth and width of the oil-can. For airplanes
on which oil-cans are found within limits, the service information
specifies an option of doing repetitive detailed and HFEC inspections
for cracks of the oil-canning and eventual repair. Doing the repair
terminates the repetitive inspections.
Repetitive eddy current inspections to detect cracks of
the dome cap at the center of the bulkhead.
Repetitive HFEC inspections to detect cracks of the ``Z''
stiffener flanges at the dome cap in the center of the bulkhead.
A detailed inspection of the bulkhead web and of the
stiffeners for existing repairs; and, depending on the findings,
repetitive HFEC or LFEC inspections of the web for cracking;
replacement of existing repairs with new repairs, and damage tolerance
inspections.
The corrective actions include repairing discrepancies
(including cracking, misdrilled fastener holes, elongated fastener
holes, corrosion, oil-cans, and existing repairs), or for certain
discrepancies, contacting Boeing for repair instructions.
The initial compliance times vary depending on inspection
type and area. The earliest initial inspection is within 375 flight
cycles after the effective date of this AD. The latest initial
inspection is within 6,000 flight cycles or 24 months after the
effective date of this AD, whichever occurs first.
The compliance times for the option, for airplanes on which oil-
cans are found within limits, of doing repetitive detailed and HFEC
inspections for cracks of the oil-canning and eventual repair are as
follows: The initial inspections are done before further flight. The
repetitive interval is 1,200 flight cycles. The repair must be done
within 12,000 flight cycles after the oil-can was found.
The repetitive inspections range from intervals not to exceed 6,000
flight cycles to intervals not to exceed 12,000 flight cycles,
depending on the inspection type and area.
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 all requirements of AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999). This proposed AD
would also require accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the Proposed AD and the Service Information.''
Changes to Existing AD
This proposed AD would retain all requirements of AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999). Since AD 99-08-23 was
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 table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Requirement in AD 99-08-23,
Amendment 39-11132 (64 FR 19879, Corresponding requirement in this
April 23, 1999) proposed AD
------------------------------------------------------------------------
paragraph (a) paragraph (g)
paragraph (b) paragraph (h)
paragraph (c) paragraph (i)
paragraph (d) paragraph (j)
------------------------------------------------------------------------
Boeing Commercial Airplanes has received an Organization
Designation Authorization (ODA). We have revised this proposed AD to
delegate the authority to approve an alternative method of compliance
for any repair required by this proposed AD to the Boeing Commercial
Airplanes ODA rather than a Designated Engineering Representative
(DER).
We have revised the date of the document specified in paragraph
(j)(1) of this proposed AD (which is a restatement of paragraph (d)(1)
of AD 99-08-23, Amendment 39-11132 (64 FR 19879, April 23, 1999)), to
November 5, 1995, as specified in the ``Incorporation of Reference''
paragraph of AD 99-08-23 (paragraph (g) of AD 99-08-23).
Differences Between the Proposed AD and the Service Information
Boeing Alert Service Bulletin 737-53A1214, Revision 4, dated
December 16, 2011, specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD affects 566 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
[[Page 38549]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
LFEC [retained actions from AD 99- 8 work-hours x $85 $0 $680............... $384,880.
08-23, Amendment 39-11132 (64 FR per hour = $680.
19879, April 23, 1999)].
Detailed visual inspection 2 work-hours x $85 0 $170............... $96,220.
[retained actions from AD 99- per hour = $170.
08[dash]23, Amendment 39-11132
(64 FR 19879, April 23, 1999)].
Detailed, HFEC, and LFEC Up to 60 0 $5,100 per $2,886,600 per
inspections of the web at the work[dash]hours x inspection cycle. inspection cycle.
``Y'' chord of the bulkhead, the $85 per hour =
web located under the outer $5,100 per
circumferential tear strap, the inspection cycle.
``Z'' stiffeners at the dome
cap, and existing repairs [new
proposed action].
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
inspections that would be required based on the results of the proposed
initial inspection. We have no way of determining the number of
aircraft that might need these inspections:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Detailed and HFEC inspections for 1 work-hour x $85 per hour = $85 $0 $85
oil[dash]canning.
LFEC or HFEC inspections for cracking......... 2 work-hours x $85 per hour = 0 170
$170.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the crack repairs specified in this proposed 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 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.
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) 99-08-23, Amendment 39-11132 (64 FR 19879, April 23, 1999), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2012-0645; Directorate Identifier
2011-NM-052-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by August 13,
2012.
(b) Affected ADs
This AD supersedes AD 99-08-23, Amendment 39-11132 (64 FR 19879,
April 23, 1999).
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes; certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by several reports of fatigue cracks in the
aft pressure bulkhead. We are issuing this AD to detect and correct
such fatigue cracking, which could result in rapid decompression of
the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Initial Inspection
This paragraph restates the initial inspection required by
paragraph (a) of AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999). Perform either inspection specified by paragraph (g)(1)
or
[[Page 38550]]
(g)(2) of this AD at the time specified in paragraph (h) of this AD.
(1) Perform a low frequency eddy current (LFEC) inspection from
the aft side of the aft pressure bulkhead to detect discrepancies
(including cracking, misdrilled fastener holes, and corrosion) of
the web of the upper section of the aft pressure bulkhead at body
station 1016 at the aft fastener row attachment to the ``Y'' chord,
from stringer 15 left to stringer 15 right, in accordance with
Boeing 737 Nondestructive Test Manual D6-37239, Part 6, Section 53-
10-54, dated December 5, 1998.
(2) Perform a detailed visual inspection of the aft fastener row
attachment to the ``Y'' chord from the forward side of the aft
pressure bulkhead to detect discrepancies (including cracking,
misdrilled fastener holes, and corrosion) of the entire web of the
aft pressure bulkhead at body station 1016.
(h) Retained Compliance Times
This paragraph restates the compliance times specified in
paragraph (b) of AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999). Perform the inspection required by paragraph (g) of this
AD at the time specified in paragraph (h)(1), (h)(2), or (h)(3) of
this AD, as applicable.
(1) For airplanes that have accumulated 40,000 or more total
flight cycles as of May 10, 1999 (the effective date of AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999)): Inspect within
375 flight cycles or 60 days after May 10, 1999, whichever occurs
later.
(2) For airplanes that have accumulated 25,000 or more total
flight cycles and fewer than 40,000 total flight cycles as of May
10, 1999 (the effective date of AD 99-08-23, Amendment 39-11132 (64
FR 19879, April 23, 1999)): Inspect within 750 flight cycles or 90
days after May 10, 1999, whichever occurs later.
(3) For airplanes that have accumulated fewer than 25,000 total
flight cycles as of May 10, 1999 (the effective date of AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999)): Inspect prior to
the accumulation of 25,750 total flight cycles.
(i) Retained Repetitive Inspections
This paragraph restates the repetitive inspections required by
paragraph (c) of AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999). Within 1,200 flight cycles after performing the initial
inspection required by paragraph (g) of this AD, and thereafter at
intervals not to exceed 1,200 flight cycles: Perform either
inspection specified by paragraph (g)(1) or (g)(2) of this AD.
(j) Retained Corrective Actions
This paragraph restates the corrective actions required by
paragraph (d) of AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999). If any discrepancy is detected during any inspection
required by paragraph (g), (h), or (i) of this AD: Prior to further
flight, accomplish the actions specified by paragraphs (j)(1) and
(j)(3) of this AD, and paragraph (j)(2) of this AD, if applicable.
(1) Perform a high frequency eddy current inspection from the
forward side of the bulkhead to detect cracking of the web at the
``Y'' chord attachment, around the entire periphery of the ``Y''
chord, in accordance with Boeing 737 Nondestructive Test Manual D6-
37239, Part 6, Section 51-00-00, Figure 23, dated November 5, 1995.
(2) If the most recent inspection performed in accordance with
paragraph (g) of this AD was not a detailed visual inspection:
Accomplish the actions specified by paragraph (g)(2) of this AD. If
the inspection was a detailed visual inspection, it is not necessary
to repeat that inspection prior to further flight.
(3) Repair any discrepancy such as cracking or corrosion or
misdrilled fastener holes using a method approved in accordance with
the procedures specified in paragraph (u) of this AD.
(k) New Requirements: Inspections of the Web at the ``Y'' Chord Upper
Bulkhead From S-15L to S-15R
At the later of the times specified in paragraphs (k)(1) and
(k)(2) of this AD: Do detailed and LFEC inspections of the aft side
of the bulkhead web, or do detailed and HFEC inspections from the
forward side of the bulkhead, and do all applicable related
investigative and corrective actions; in accordance with Part 1 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011, except as required
by paragraphs (r)(1) and (r)(3) of this AD. Inspect for cracks,
incorrectly drilled fastener holes, and elongated fastener holes. Do
all applicable related investigative and corrective actions before
further flight. Repeat the inspections at the applicable times
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011.
(1) Prior to the accumulation of 25,000 total flight cycles.
(2) Except as required by paragraphs (r)(2) and (r)(4) of this
AD, at the later of the times specified in the ``Compliance Time''
column in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011.
(l) New Requirements: Inspections of the Web at the ``Y'' Chord in the
Lower Bulkhead From S-15L to S-15R
Except as required by paragraphs (r)(2) and (r)(5) of this AD,
at the applicable time specified in table 2 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do detailed and eddy current
inspections of the web from the forward or aft side of the bulkhead
for cracks, incorrectly drilled fasteners, and elongated fasteners,
in accordance with Part III of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1214, Revision 4, dated
December 16, 2011, except as required by paragraphs (r)(1) and
(r)(3) of this AD. If any crack, incorrectly drilled fastener,
elongated fastener, or corrosion is found, before further flight,
repair the web using a method approved in accordance with the
procedures specified in paragraph (u) of this AD. Repeat the
inspections at the applicable times specified in table 2 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011.
(m) New Requirements: One-Time Inspection Under the Tear Strap
Except as required by paragraphs (r)(2) and (r)(5) of this AD,
at the applicable time specified in table 3 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do a one-time LFEC inspection
for cracks on the aft side of the bulkhead of the web located under
the outer circumferential tear strap, or do a one-time HFEC
inspection for cracks from the forward side of the bulkhead of the
web located under the outer circumferential tear strap, in
accordance with Part II of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011, except as required by paragraph (r)(1) of this AD. If any
cracking is found, before further flight, repair the bulkhead using
a method approved in accordance with the procedures specified in
paragraph (u) of this AD.
(n) New Requirements: Inspection for Oil-Canning
Except as required by paragraph (r)(2) of this AD, at the
applicable time specified in table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do a detailed inspection from
the aft side of the bulkhead for oil-canning and do all applicable
related investigative and corrective actions, in accordance with
Part II of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011, except as
required by paragraph (r)(1) of this AD. Do all related
investigative and corrective actions before further flight.
Thereafter, repeat the inspection at the applicable times specified
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011.
For oil-cans found within the limits specified in Part II of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011: In lieu of installing
the repair before further flight, at the applicable times specified
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011,
do initial and repetitive detailed and HFEC inspections for cracks
of the oil-canning and install the repair, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011. If any crack is found,
before further flight, repair the cracking using a method approved
in accordance with the procedures specified in paragraph (u) of this
AD. Installing the repair terminates the repetitive inspections for
cracks.
[[Page 38551]]
(o) New Requirements: Inspection of the Dome Cap at the Center of the
Bulkhead
Except as required by paragraphs (r)(2) and (r)(5) of this AD,
at the applicable time specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do an eddy current inspection
to detect any cracking of the dome cap at the center of the
bulkhead, and do all applicable corrective actions, in accordance
with Part IV of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011.
Do all corrective actions before further flight. Repeat the
inspection at the times specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011.
(p) New Requirements: Inspection of the Forward Flange of the ``Z''
Stiffeners at the Dome Cap
Except as required by paragraphs (r)(2) and (r)(5) of this AD,
at the applicable time specified in table 6 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do an HFEC inspection to detect
any cracking of the ``Z'' stiffener flanges at the dome cap in the
center of the bulkhead, in accordance with Part V of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011, except as required by
paragraph (r)(1) of this AD. If any crack is found, before further
flight, repair the flanges using a method approved in accordance
with the procedures specified in paragraph (u) of this AD. Repeat
the inspection at the applicable times specified in table 6 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011.
(q) New Requirement: Inspection for Existing Repairs on the Bulkhead
Except as required by paragraph (r)(2) of this AD, at the
applicable time specified in table 7 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do a detailed inspection of the
bulkhead web and stiffeners for existing repairs, in accordance with
Part VI of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011, except as
required by paragraph (r)(1) of this AD.
(1) If any repair identified in the ``Condition'' column of
table 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011, is found
and the ``Reference'' column refers to Appendix A, B, C, or D of
that service bulletin: At the applicable times specified in table 8
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011, except as required
by paragraph (r)(2) of this AD, do a HFEC inspection or a LFEC
inspection of the web for cracking, in accordance with Appendix A,
B, C, or D, as applicable, of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011. If any cracking is
found, before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (u) of this
AD. Repeat the inspections, thereafter, at the applicable intervals
specified in table 8 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011.
(2) If any repair identified in the ``Condition'' column of
table 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011, is found
and the ``Reference'' column refers to Appendix E of that service
bulletin: At the applicable times specified in table 8 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011, except as required by paragraph
(r)(2) of this AD, remove the repair and replace with a new repair,
in accordance with Appendix E of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011.
(3) If any non-SRM (structural repair manual) repair is found
and the repair does not have FAA-approved damage tolerance
inspections, except as required by paragraph (r)(2) of this AD, at
the applicable time specified in table 7 of Paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Contact the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) that has been
authorized by the Manager, Seattle ACO, for damage tolerance
inspections. Do those damage tolerance inspections at the times
given using a method approved in accordance with the procedures
specified in paragraph (u) of this AD.
(r) Exceptions to the Service Bulletin
(1) Where Boeing Alert Service Bulletin 737-53A1214, Revision 4,
dated December 16, 2011, specifies to contact Boeing for repair
instructions: Before further flight, repair using a method approved
in accordance with the procedures specified in paragraph (u) of this
AD.
(2) Where Boeing Alert Service Bulletin 737-53A1214, Revision 4,
dated December 16, 2011, specifies a compliance time ``after the
date of Revision 1 to this service bulletin,'' ``from the date of
Revision 3 of this service bulletin,'' ``after the date of Revision
3 to this service bulletin,'' or ``of the effective date of AD 99-
08-23,'' this AD requires compliance within the specified compliance
time after the effective date of this AD.
(3) Access and restoration procedures specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011, are not required by
this AD. Operators may do those procedures following their
maintenance practices.
(4) Where table 1 of paragraph 1.E., ``Compliance'' of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011, specifies a compliance time relative to actions done ``in
accordance with paragraph (a)(2) of AD 99-08-23,'' this AD requires
compliance within the specified compliance time relative to actions
specified in paragraph (g)(2) of this AD.
(5) Where the Condition columns in tables 2, 3, 5, and 6 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011, refer to total
flight cycles, this AD applies to the airplanes with the specified
total flight cycles as of the effective date of this AD.
(s) Terminating Action
Accomplishment of the requirements of paragraphs (k) through (q)
of this AD terminates the requirements of paragraphs (g) through (j)
of this AD.
(t) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (k) through (s) of this AD, if the actions were performed
before the effective date of this AD using the service bulletins
specified in paragraphs (t)(1) through (t)(4) of this AD.
(1) Boeing Alert Service Bulletin 737-53A1214, dated June 17,
1999.
(2) Boeing Alert Service Bulletin 737-53A1214, Revision 1, dated
June 22, 2000.
(3) Boeing Alert Service Bulletin 737-53A1214, Revision 2, dated
May 24, 2001.
(4) Boeing Alert Service Bulletin 737-53A1214, Revision 3, dated
January 19, 2011.
(u) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
ACO, send it to the attention of the person identified in 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 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 previously in accordance with AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999), are approved as
AMOCs for the corresponding provisions of this AD.
(v) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: (425) 917-6440; fax: (425) 917-6590; email:
alan.pohl@faa.gov.
[[Page 38552]]
(2) 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; 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.
Issued in Renton, Washington, on June 18, 2012.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-15601 Filed 6-27-12; 8:45 am]
BILLING CODE 4910-13-P
