Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes, 48594-48597 [E7-16657]
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48594
Federal Register / Vol. 72, No. 164 / Friday, August 24, 2007 / Proposed Rules
circuit breakers through the right utility bus
switch and do all other specified actions as
applicable, by accomplishing all of the
applicable actions specified in the
Accomplishment Instructions of Boeing
Service Bulletin 767–24–0148, dated
September 14, 2006; Boeing Service Bulletin
767–24–0149, dated September 14, 2006;
Boeing Service Bulletin 767–24–0150, dated
September 21, 2006; and Boeing Service
Bulletin 767–24–0151, dated September 14,
2006; as applicable. The other specified
actions must be done before further flight
after installing the new relay(s) and wiring.
Installing New Relays on Certain Model
767–400ER Series Airplanes
(h) For the airplanes identified in
paragraph (c)(3) of this AD: Within 60
months after the effective date of this AD,
install a new relay and wiring to allow the
flightcrew to turn off electrical power to
some of the IFE systems and certain circuit
breakers through the left utility bus switch
and do all other specified actions, by
accomplishing all of the actions specified in
the Accomplishment Instructions of Boeing
Service Bulletin 767–24–0147, dated
February 20, 2003. The other specified
actions must be done before further flight
after installing the new relay and wiring.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on August
14, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–16661 Filed 8–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29031; Directorate
Identifier 2007–NM–130–AD]
rfrederick on PROD1PC67 with PROPOSALS
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, –800, and
–900 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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Jkt 211001
Notice of proposed rulemaking
(NPRM).
ACTION:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 737–600, –700,
–700C, –800, and –900 series airplanes.
This proposed AD would require
repetitive inspections of either the aft
side or forward side of the aft pressure
bulkhead for oil can conditions or
bulges, a one-time inspection of the aft
pressure bulkhead to identify any
previously installed web repair, and
corrective actions if necessary. This
proposed AD results from web oil can
conditions found on the aft pressure
bulkhead of several airplanes. We are
proposing this AD to detect and correct
oil can conditions, bulges, or previous
repairs in the aft pressure bulkhead,
which could lead to web cracks and
consequently result in rapid
decompression of the airplane.
DATES: We must receive comments on
this proposed AD by October 9, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• 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.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Howard Hall, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6430; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
PO 00000
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ADDRESSES section. Include the docket
number ‘‘FAA–2007–29031; Directorate
Identifier 2007–NM–130–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
ground floor of the West Building at the
DOT street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
the Docket Management System receives
them.
Discussion
We have received a report indicating
that ‘‘oil cans’’ or ‘‘bulges’’ have been
found on the aft pressure bulkhead web
of several Boeing Model 737–600, –700,
–700C, –800, and –900 series airplanes.
(An oil can is defined as an area on the
pressure dome web that has visibly
deviated forward from the initial
contour of the pressured dome web. A
bulge is defined as an area on the
pressure dome web that has visibly
deviated aft from the initial contour of
the pressure dome web.) Oil can
conditions or bulges in the aft pressure
bulkhead, if not corrected, could lead to
web cracks and consequently result in
rapid decompression of the airplane.
In addition, some operators may have
previously repaired an oil can condition
in accordance with the Boeing 737–600/
700/700C/800/900 Structural Repair
Manuals (SRMs). The latest revision of
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the SRM currently requires
accomplishing an initial nondestructive
testing (NDT) inspection of the repair
and incorporating repetitive
supplemental inspections of the repair
into the airplane’s maintenance
program. Repair procedures in earlier
revisions of the SRMs did not specify
doing an initial NDT inspection and/or
repetitive supplemental inspections. If
the initial NDT inspection and
repetitive supplemental inspections of
the repair are not accomplished, web
cracks could also develop and
consequently result in loss of cabin
pressurization.
rfrederick on PROD1PC67 with PROPOSALS
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 737–53A1253, dated
May 18, 2007. The service bulletin
describes procedures for doing
repetitive general visual inspections of
either the aft side or forward side of the
aft pressure bulkhead for oil can
conditions or bulges, a one-time general
visual inspection of the aft pressure
bulkhead to identify any previously
installed web repair, and corrective
actions as applicable. The corrective
actions include:
• If the oil can condition is within a
certain limit, (1) doing repetitive
inspections of aft pressure bulkhead for
web cracks until an oil can condition is
repaired, or (2) before further flight,
doing one-time NDT inspections of aft
pressure bulkhead for web cracks and
repairing the oil can condition.
• If the oil can condition is beyond a
certain limit, doing a one-time NDT
inspection of the affected web bay at the
fastener locations where the web
intersects the surrounding structure for
cracks and repairing the oil can
condition.
• If existing bulkhead repairs or
bulging of tear straps prevent
accomplishing low and high frequency
eddy current inspections, contacting
Boeing for instructions.
• Repairing any cracks or bulges
found during any inspection and
contacting Boeing for repair instructions
if necessary.
• If a previously installed oil can
repair is found, doing one-time NDT
inspections of the web at the
surrounding structure interfaces for
cracks.
• If follow-on supplemental
inspections of a previously installed
repair are not being accomplished,
determining the FAA-approved, followon inspection procedures, thresholds,
and repetitive intervals and
incorporating them into the airplane
maintenance program.
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13:20 Aug 23, 2007
Jkt 211001
Table 1 of paragraph 1.E. of the
service bulletin recommends the
following compliance times for the
general visual inspections for oil can
conditions or bulges in the aft pressure
bulkhead: (1) The initial inspection at or
before 15,000 total flight cycles or
within 1,200 flight cycles from the
release date of the bulletin, (2) the first
repetitive inspection thereafter at or
before 10,000 flight cycles, and (3) the
subsequent repetitive general visual
inspections thereafter at or before 6,000
flight cycles. Table 1 also recommends
repairing an oil can condition at or
before 12,000 flight cycles, or before
further flight, depending upon the
extent of the oil can condition. Table 1
also recommends repairing any crack or
bulge before further flight.
Table 2 of paragraph 1.E. of the
service bulletin specifies a compliance
time of 15,000 total flight cycles or
within 1,200 flight cycles after the date
on the service bulletin, for doing the
one-time general visual inspection to
identify repairs to the gore web (i.e., the
tapered web segments). If any repair is
found that does not have follow-on
supplemental inspections, Table 2
specifies to determine the FAAapproved, follow-on inspection
procedures, thresholds, and repetitive
intervals and to incorporate them into
the airplane maintenance program
within 12 months after accomplishing
the inspection given in Section 53–80–
08–2R of the Boeing 737–600/700/700C/
800/900 SRMs.
For Model 737–700 and –800 series
airplanes on which Boeing Business Jet
(BBJ) Lower Cabin Altitude
Modification has been incorporated in
accordance with Supplemental Type
Certificate (STC) ST01697SE: Paragraph
1.E. of the service bulletin recommends
that all initial compliance times
(thresholds) specified in flight cycles be
reduced to one-half of those specified in
the service bulletin, and that all repeat
interval compliance times specified in
flight cycles be reduced to one-quarter
of those specified in the service bulletin.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other airplanes of this same
type design. For this reason, we are
proposing this AD, which would require
accomplishing the actions specified in
the service information described
previously, except as discussed under
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48595
‘‘Differences Between the Proposed AD
and Service Bulletin.’’
Differences Between the Proposed AD
and Service Bulletin
The service bulletin 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:
• Using a method that we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by an
Authorized Representative for the
Boeing Commercial Airplanes
Delegation Option Authorization
Organization whom we have authorized
to make those findings.
The service bulletin specifies to
contact Boeing for further instructions
in developing an FAA-approved
supplemental inspection program if an
aft pressure bulkhead is found that does
not have supplemental inspections
specified in either the Boeing 737–600/
700/700C/800/900 SRMs or the service
bulletin. This proposed AD would
instead require contacting the Manager,
Seattle Aircraft Certification Office, or
an Authorized Representative for the
Boeing Commercial Airplanes
Delegation Option Authorization
Organization.
If any repair is found that does not
have follow-on supplemental
inspections, Table 2 of paragraph 1.E. of
the service bulletin specifies to
determine the FAA-approved follow-on
inspections procedures, thresholds, and
repetitive intervals and to incorporate
them into the airplane maintenance
program within 12 months after
accomplishing the inspection in Section
53–80–08–2R of the Boeing 737–600/
700/700C/800/900 SRMs. This proposed
AD, however, would require that those
corrective actions, if applicable, be done
within 12 months after accomplishing
the one-time general visual inspection
of the aft pressure bulkhead for any
previously installed web repair.
Tables 1 and 2 of paragraph 1.E. of the
service bulletin specify a compliance
time of 15,000 total flight cycles or
within 1,200 flight cycles from the
release date or after the date on the
service bulletin, for the general visual
inspections. This proposed AD would
require accomplishing the applicable
inspection at the later of those
compliance times. This proposed AD
would also require starting the
compliance time from the effective date
of this AD, not from the service bulletin
date.
Although the service bulletin
specifies to submit certain information
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Federal Register / Vol. 72, No. 164 / Friday, August 24, 2007 / Proposed Rules
to the manufacturer, this proposed AD
does not include that requirement. We
do not need this information from
operators.
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
737–53A1253, dated May 18, 2007, except as
provided by paragraphs (h) and (i) of this AD.
List of Subjects in 14 CFR Part 39
Costs of Compliance
There are about 1,755 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about
600 airplanes of U.S. registry. The
proposed inspection would take about 6
work hours per airplane, at an average
labor rate of $80 per work hour. Based
on these figures, the estimated cost of
the proposed AD for U.S. operators is
$288,000, or $480 per airplane, per
inspection cycle.
Air transportation, Aircraft, Aviation
safety, Safety.
(g) Where Tables 1 and 2 of paragraph 1.E.
of Boeing Alert Service Bulletin 737–
53A1253, dated May 18, 2007, specify a
compliance time of ‘‘at or before 15,000 total
flight cycles or within 1,200 flight cycles’’ for
the general visual inspections, this AD would
require accomplishing the applicable
inspection at the later of those compliance
times. Where Tables 1 and 2 of paragraph
1.E. of the service bulletin specify counting
the compliance time from the ‘‘release date
of this service bulletin’’ or ‘‘after the date on
this service bulletin,’’ this proposed requires
starting the compliance time from the
effective date of this AD. Where Table 2 of
paragraph 1.E. of the service bulletin
specifies to determine the FAA-approved,
follow-on inspection procedures, thresholds,
and repeat intervals and to incorporate them
into the airplane maintenance program
within 12 months after accomplishing the
inspection given in Section 53–80–08–2R of
the Boeing 737–600/700/700C/800/900
Structural Repair Manuals (SRMs), this AD
requires that those corrective actions, if
applicable, be done within 12 months after
accomplishing the one-time general visual
inspection of the aft pressure bulkhead for
any previously installed web repair as
required by paragraph (f) of this AD.
rfrederick on PROD1PC67 with PROPOSALS
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); and
3. 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
VerDate Aug<31>2005
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Jkt 211001
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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2007–29031;
Directorate Identifier 2007–NM–130–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by October 9, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737–
600, –700, –700C, –800, and –900 series
airplanes, certificated in any category; as
identified in Boeing Alert Service Bulletin
737–53A1253, dated May 18, 2007.
Unsafe Condition
(d) This AD results from web oil can
conditions found on the aft pressure
bulkhead of several airplanes. We are issuing
this AD to detect and correct oil can
conditions, bulges, or previous repairs in the
aft pressure bulkhead, which could lead to
web cracks and consequently result in rapid
decompression of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Repetitive Inspections
(f) At the applicable times specified in
paragraph 1.E. of Boeing Alert Service
Bulletin 737–53A1253, dated May 18, 2007,
except as provided by paragraph (g) of this
AD: Do repetitive general visual inspections
of either the aft side or forward side of the
aft pressure bulkhead for oil can conditions
or bulges and a one-time general visual
inspection of the aft pressure bulkhead to
identify any previously installed web repair,
and do all applicable corrective actions, by
accomplishing all of the applicable actions
specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
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Exceptions to Compliance Times
Exceptions to Corrective Actions
(h) If any crack or bulge is found during
any inspection required by paragraph (f) of
this AD and Boeing Alert Service Bulletin
737–53A1253, dated May 18, 2007, specifies
to contact Boeing for repair instructions,
before further flight, repair according to a
method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA, or
according to data meeting the certification
basis of the airplane approved by an
Authorized Representative for the Boeing
Delegation Option Authorization
Organization who 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. If a previously
installed aft pressure bulkhead web repair is
found during any inspection required by
paragraph (f) of this AD, and the FAAapproved supplemental inspection program
cannot be determined from either the Boeing
737–600/700/700C/800/900 SRMs or the
service bulletin, and the service bulletin
specifies to contact Boeing for further
instructions, within 12 months after
accomplishing the inspection, contact the
Manager, SACO, or an Authorized
Representative for the Boeing Commercial
Airplanes Delegation Option Authorization
Organization to develop a supplemental
inspection program.
No Reporting Requirement
(i) Although Boeing Alert Service Bulletin
737–53A1253, dated May 18, 2007, specifies
to submit certain information to the
manufacturer, this AD does not require that
action.
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Federal Register / Vol. 72, No. 164 / Friday, August 24, 2007 / Proposed Rules
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(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 an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who 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 14 CFR
25.571, Amendment 45, and the approval
must specifically refer to this AD.
Issued in Renton, Washington, on August
14, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–16657 Filed 8–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29043; Directorate
Identifier 2007–NM–177–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–300, –400, and –500 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
rfrederick on PROD1PC67 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Boeing Model 737–300, –400, and –500
series airplanes. This proposed AD
would require revising the FAAapproved maintenance inspection
program to include inspections that will
give no less than the required damage
tolerance rating for each structural
significant item (SSI), doing repetitive
inspections to detect cracks of all SSIs,
and repairing cracked structure. This
proposed AD results from a report of
incidents involving fatigue cracking and
corrosion in transport category airplanes
that are approaching or have exceeded
VerDate Aug<31>2005
14:16 Aug 23, 2007
Jkt 211001
their design service objective. We are
proposing this AD to maintain the
continued structural integrity of the
entire fleet of Model 737–300, –400, and
–500 series airplanes.
DATES: We must receive comments on
this proposed AD by October 9, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• 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.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6440; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2007–29043; Directorate
Identifier 2007–NM–177–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
PO 00000
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Sfmt 4702
48597
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
ground level of the West Building at the
DOT street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
the Docket Management System receives
them.
Discussion
In the early 1980’s, as part of its
continuing work to maintain the
structural integrity of older transport
category airplanes, we concluded that
the incidence of fatigue cracking may
increase as these airplanes reach or
exceed their design service objective
(DSO). In light of this, and as a result
of increased utilization, and longer
operational lives, we determined that a
supplemental structural inspection
program (SSIP) was necessary to
maintain the continued structural
integrity for all airplanes in the
transport fleet.
Issuance of Advisory Circular (AC)
As a follow-on from that
determination, we issued AC No. 91–56,
‘‘Supplemental Structural Inspection
Program for Large Transport Category
Airplanes,’’ dated May 6, 1981. That AC
provides guidance material to
manufacturers and operators for use in
developing a continuing structural
integrity program to ensure safe
operation of older airplanes throughout
their operational lives. This guidance
material applies to transport airplanes
that were certified under the fail-safe
requirements of part 4b (‘‘Airplane
Airworthiness, Transport Categories’’) of
the Civil Air Regulations or damage
tolerance structural requirements of part
25 (‘‘Airworthiness Standards:
Transport Category Airplanes’’) of the
Federal Aviation Regulations (FAR) (14
CFR part 25), and that have a maximum
gross weight greater than 75,000
pounds. The procedures set forth in that
AC are applicable to transport category
E:\FR\FM\24AUP1.SGM
24AUP1
]]>Agencies
[Federal Register Volume 72, Number 164 (Friday, August 24, 2007)]
[Proposed Rules]
[Pages 48594-48597]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-16657]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29031; Directorate Identifier 2007-NM-130-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-600, -700, -700C, -
800, and -900 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 737-600, -700, -700C, -800, and -900 series
airplanes. This proposed AD would require repetitive inspections of
either the aft side or forward side of the aft pressure bulkhead for
oil can conditions or bulges, a one-time inspection of the aft pressure
bulkhead to identify any previously installed web repair, and
corrective actions if necessary. This proposed AD results from web oil
can conditions found on the aft pressure bulkhead of several airplanes.
We are proposing this AD to detect and correct oil can conditions,
bulges, or previous repairs in the aft pressure bulkhead, which could
lead to web cracks and consequently result in rapid decompression of
the airplane.
DATES: We must receive comments on this proposed AD by October 9, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
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.
Fax: (202) 493-2251.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for the service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Howard Hall, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6430; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
29031; Directorate Identifier 2007-NM-130-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The
Docket Operations office (telephone (800) 647-5527) is located on the
ground floor of the West Building at the DOT street address stated in
the ADDRESSES section. Comments will be available in the AD docket
shortly after the Docket Management System receives them.
Discussion
We have received a report indicating that ``oil cans'' or
``bulges'' have been found on the aft pressure bulkhead web of several
Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. (An
oil can is defined as an area on the pressure dome web that has visibly
deviated forward from the initial contour of the pressured dome web. A
bulge is defined as an area on the pressure dome web that has visibly
deviated aft from the initial contour of the pressure dome web.) Oil
can conditions or bulges in the aft pressure bulkhead, if not
corrected, could lead to web cracks and consequently result in rapid
decompression of the airplane.
In addition, some operators may have previously repaired an oil can
condition in accordance with the Boeing 737-600/700/700C/800/900
Structural Repair Manuals (SRMs). The latest revision of
[[Page 48595]]
the SRM currently requires accomplishing an initial nondestructive
testing (NDT) inspection of the repair and incorporating repetitive
supplemental inspections of the repair into the airplane's maintenance
program. Repair procedures in earlier revisions of the SRMs did not
specify doing an initial NDT inspection and/or repetitive supplemental
inspections. If the initial NDT inspection and repetitive supplemental
inspections of the repair are not accomplished, web cracks could also
develop and consequently result in loss of cabin pressurization.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-53A1253, dated
May 18, 2007. The service bulletin describes procedures for doing
repetitive general visual inspections of either the aft side or forward
side of the aft pressure bulkhead for oil can conditions or bulges, a
one-time general visual inspection of the aft pressure bulkhead to
identify any previously installed web repair, and corrective actions as
applicable. The corrective actions include:
If the oil can condition is within a certain limit, (1)
doing repetitive inspections of aft pressure bulkhead for web cracks
until an oil can condition is repaired, or (2) before further flight,
doing one-time NDT inspections of aft pressure bulkhead for web cracks
and repairing the oil can condition.
If the oil can condition is beyond a certain limit, doing
a one-time NDT inspection of the affected web bay at the fastener
locations where the web intersects the surrounding structure for cracks
and repairing the oil can condition.
If existing bulkhead repairs or bulging of tear straps
prevent accomplishing low and high frequency eddy current inspections,
contacting Boeing for instructions.
Repairing any cracks or bulges found during any inspection
and contacting Boeing for repair instructions if necessary.
If a previously installed oil can repair is found, doing
one-time NDT inspections of the web at the surrounding structure
interfaces for cracks.
If follow-on supplemental inspections of a previously
installed repair are not being accomplished, determining the FAA-
approved, follow-on inspection procedures, thresholds, and repetitive
intervals and incorporating them into the airplane maintenance program.
Table 1 of paragraph 1.E. of the service bulletin recommends the
following compliance times for the general visual inspections for oil
can conditions or bulges in the aft pressure bulkhead: (1) The initial
inspection at or before 15,000 total flight cycles or within 1,200
flight cycles from the release date of the bulletin, (2) the first
repetitive inspection thereafter at or before 10,000 flight cycles, and
(3) the subsequent repetitive general visual inspections thereafter at
or before 6,000 flight cycles. Table 1 also recommends repairing an oil
can condition at or before 12,000 flight cycles, or before further
flight, depending upon the extent of the oil can condition. Table 1
also recommends repairing any crack or bulge before further flight.
Table 2 of paragraph 1.E. of the service bulletin specifies a
compliance time of 15,000 total flight cycles or within 1,200 flight
cycles after the date on the service bulletin, for doing the one-time
general visual inspection to identify repairs to the gore web (i.e.,
the tapered web segments). If any repair is found that does not have
follow-on supplemental inspections, Table 2 specifies to determine the
FAA-approved, follow-on inspection procedures, thresholds, and
repetitive intervals and to incorporate them into the airplane
maintenance program within 12 months after accomplishing the inspection
given in Section 53-80-08-2R of the Boeing 737-600/700/700C/800/900
SRMs.
For Model 737-700 and -800 series airplanes on which Boeing
Business Jet (BBJ) Lower Cabin Altitude Modification has been
incorporated in accordance with Supplemental Type Certificate (STC)
ST01697SE: Paragraph 1.E. of the service bulletin recommends that all
initial compliance times (thresholds) specified in flight cycles be
reduced to one-half of those specified in the service bulletin, and
that all repeat interval compliance times specified in flight cycles be
reduced to one-quarter of those specified in the service bulletin.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the Proposed AD and Service Bulletin.''
Differences Between the Proposed AD and Service Bulletin
The service bulletin 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:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
The service bulletin specifies to contact Boeing for further
instructions in developing an FAA-approved supplemental inspection
program if an aft pressure bulkhead is found that does not have
supplemental inspections specified in either the Boeing 737-600/700/
700C/800/900 SRMs or the service bulletin. This proposed AD would
instead require contacting the Manager, Seattle Aircraft Certification
Office, or an Authorized Representative for the Boeing Commercial
Airplanes Delegation Option Authorization Organization.
If any repair is found that does not have follow-on supplemental
inspections, Table 2 of paragraph 1.E. of the service bulletin
specifies to determine the FAA-approved follow-on inspections
procedures, thresholds, and repetitive intervals and to incorporate
them into the airplane maintenance program within 12 months after
accomplishing the inspection in Section 53-80-08-2R of the Boeing 737-
600/700/700C/800/900 SRMs. This proposed AD, however, would require
that those corrective actions, if applicable, be done within 12 months
after accomplishing the one-time general visual inspection of the aft
pressure bulkhead for any previously installed web repair.
Tables 1 and 2 of paragraph 1.E. of the service bulletin specify a
compliance time of 15,000 total flight cycles or within 1,200 flight
cycles from the release date or after the date on the service bulletin,
for the general visual inspections. This proposed AD would require
accomplishing the applicable inspection at the later of those
compliance times. This proposed AD would also require starting the
compliance time from the effective date of this AD, not from the
service bulletin date.
Although the service bulletin specifies to submit certain
information
[[Page 48596]]
to the manufacturer, this proposed AD does not include that
requirement. We do not need this information from operators.
Costs of Compliance
There are about 1,755 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 600 airplanes of
U.S. registry. The proposed inspection would take about 6 work hours
per airplane, at an average labor rate of $80 per work hour. Based on
these figures, the estimated cost of the proposed AD for U.S. operators
is $288,000, or $480 per airplane, per inspection cycle.
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); and
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2007-29031; Directorate Identifier 2007-NM-
130-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
9, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-600, -700, -700C, -800,
and -900 series airplanes, certificated in any category; as
identified in Boeing Alert Service Bulletin 737-53A1253, dated May
18, 2007.
Unsafe Condition
(d) This AD results from web oil can conditions found on the aft
pressure bulkhead of several airplanes. We are issuing this AD to
detect and correct oil can conditions, bulges, or previous repairs
in the aft pressure bulkhead, which could lead to web cracks and
consequently result in rapid decompression of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Repetitive Inspections
(f) At the applicable times specified in paragraph 1.E. of
Boeing Alert Service Bulletin 737-53A1253, dated May 18, 2007,
except as provided by paragraph (g) of this AD: Do repetitive
general visual inspections of either the aft side or forward side of
the aft pressure bulkhead for oil can conditions or bulges and a
one-time general visual inspection of the aft pressure bulkhead to
identify any previously installed web repair, and do all applicable
corrective actions, by accomplishing all of the applicable actions
specified in the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1253, dated May 18, 2007, except as provided by
paragraphs (h) and (i) of this AD.
Exceptions to Compliance Times
(g) Where Tables 1 and 2 of paragraph 1.E. of Boeing Alert
Service Bulletin 737-53A1253, dated May 18, 2007, specify a
compliance time of ``at or before 15,000 total flight cycles or
within 1,200 flight cycles'' for the general visual inspections,
this AD would require accomplishing the applicable inspection at the
later of those compliance times. Where Tables 1 and 2 of paragraph
1.E. of the service bulletin specify counting the compliance time
from the ``release date of this service bulletin'' or ``after the
date on this service bulletin,'' this proposed requires starting the
compliance time from the effective date of this AD. Where Table 2 of
paragraph 1.E. of the service bulletin specifies to determine the
FAA-approved, follow-on inspection procedures, thresholds, and
repeat intervals and to incorporate them into the airplane
maintenance program within 12 months after accomplishing the
inspection given in Section 53-80-08-2R of the Boeing 737-600/700/
700C/800/900 Structural Repair Manuals (SRMs), this AD requires that
those corrective actions, if applicable, be done within 12 months
after accomplishing the one-time general visual inspection of the
aft pressure bulkhead for any previously installed web repair as
required by paragraph (f) of this AD.
Exceptions to Corrective Actions
(h) If any crack or bulge is found during any inspection
required by paragraph (f) of this AD and Boeing Alert Service
Bulletin 737-53A1253, dated May 18, 2007, specifies to contact
Boeing for repair instructions, before further flight, repair
according to a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA, or according to data meeting the
certification basis of the airplane approved by an Authorized
Representative for the Boeing Delegation Option Authorization
Organization who 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. If a previously installed aft
pressure bulkhead web repair is found during any inspection required
by paragraph (f) of this AD, and the FAA-approved supplemental
inspection program cannot be determined from either the Boeing 737-
600/700/700C/800/900 SRMs or the service bulletin, and the service
bulletin specifies to contact Boeing for further instructions,
within 12 months after accomplishing the inspection, contact the
Manager, SACO, or an Authorized Representative for the Boeing
Commercial Airplanes Delegation Option Authorization Organization to
develop a supplemental inspection program.
No Reporting Requirement
(i) Although Boeing Alert Service Bulletin 737-53A1253, dated
May 18, 2007, specifies to submit certain information to the
manufacturer, this AD does not require that action.
[[Page 48597]]
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Seattle ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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 an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who 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 14 CFR 25.571, Amendment 45, and the approval
must specifically refer to this AD.
Issued in Renton, Washington, on August 14, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-16657 Filed 8-23-07; 8:45 am]
BILLING CODE 4910-13-P
