Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 57890-57892 [E7-20048]
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57890
Federal Register / Vol. 72, No. 196 / Thursday, October 11, 2007 / Proposed Rules
VENUE INFORMATION
Registration closing
date
Location
Address
Date
Fairbanks, Alaska .............................................
Pioneer Park, The Alaska Centennial Center
for the Arts, 2300 Airport Road Fairbanks,
AK 99701.
October 24, 2007 ......
Registration
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
This proposed AD would require
repetitive inspections for cracking in
and around the upper and lower hinge
cutouts of the forward entry and
forward galley service doorways, and
corrective actions if necessary. This
proposed AD results from multiple
reports of cracks found in the skin,
bearstrap, and/or frame outer chord in
the hinge cutout areas of the forward
entry and forward galley service
doorways. We are proposing this AD to
detect and correct such cracking, which
could result in rapid decompression of
the airplane.
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–2007–0024; Directorate
Identifier 2007–NM–086–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.
SBA respectfully requests that any
elected or appointed representative of
the tribal communities that are
interested in attending please preregister in advance and indicate
whether you would like to testify at the
hearing. Registration requests should be
received by SBA at least 5 business days
prior to the tribal consultation meeting
date. Please contact Ms. Delcine
Montgomery of SBA’s Office of Native
American Affairs in writing at
Delcine.Montgomery@SBA.gov or by
facsimile to 202/481–1597. If you are
interested in testifying please include
the following information relating to the
person testifying: Name, Organization
affiliation, Address, Telephone number,
E-mail address and Fax number. SBA
will attempt to accommodate all
interested parties that wish to present
testimony. Based on the number of
registrants it may be necessary to
impose time limits to ensure that
everyone who wishes to testify has the
opportunity to do so. SBA will confirm
in writing the registration of presenters
and attendees.
Authority: 15 U.S.C. 634.
Stephen D. Kong,
Deputy General Counsel.
[FR Doc. E7–19962 Filed 10–10–07; 8:45 am]
BILLING CODE 8025–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0024; Directorate
Identifier 2007–NM–086–AD]
RIN 2120–AA64
mstockstill on PROD1PC66 with PROPOSALS
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
VerDate Aug<31>2005
14:15 Oct 10, 2007
Jkt 214001
We must receive comments on
this proposed AD by November 26,
2007.
DATES:
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.
ADDRESSES:
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:
PO 00000
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October 17, 2007.
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 multiple reports of
cracks found in the skin, bearstrap, and/
or frame outer chord in the hinge cutout
areas of the forward entry and forward
galley service doorways. Cracks in the
forward entry door bearstrap were
reported on an airplane with as few as
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57891
Federal Register / Vol. 72, No. 196 / Thursday, October 11, 2007 / Proposed Rules
24,538 total flight cycles. Cracks in the
forward galley service door bearstrap
were reported on an airplane with as
few as 44,938 total flight cycles. One
operator reported a severed bearstrap, a
severed station (STA) 291.5 frame, and
a 14.5-inch crack in the skin at the
lower hinge cutout of the forward galley
service doorway. The airplane had
accumulated 61,297 total flight cycles.
Such cracking, if not corrected, could
result in rapid decompression of the
airplane.
The fatigue cracks are caused by
cyclic cabin pressure loads and are not
due to manufacturing defects in the
bearstrap. The unsafe condition is
unrelated to any previous investigation
related to suspected unapproved parts.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 737–53A1200, dated
April 13, 2006. The service bulletin
describes procedures for repetitive
inspections for cracking in and around
the upper and lower hinge cutouts of
the forward entry and forward galley
service doorways. The service bulletin
describes the following inspections:
• External detailed inspection of the
skin;
• High frequency eddy current
(HFEC) hole probe inspection of the
skin, bonded doubler, bearstrap, and
frame chord at specified fastener
locations;
• HFEC hole probe inspection of the
skin, bonded doubler, and bearstrap at
specified fastener locations aft of the
frame chord;
• HFEC inspection of the skin hinge
cutout trim;
• Low frequency eddy current (LFEC)
hole probe inspection of the skin,
bonded doubler, and bearstrap at
specific fastener locations aft of the
frame chord;
• LFEC hole probe inspection of the
skin, bonded doubler, bearstrap, and
frame chord at specific fastener
locations.
The service bulletin provides two
options for the inspections, as follows:
COMPLIANCE TIMES
Inspections
Threshold, in total flight
cycles
A 1 ............
External detailed inspection; HFEC inspection of the skin
hinge cutout trim; and HFEC rotary probe inspection of
the entire zone.
External detailed inspection; HFEC inspection of the skin
hinge cutout trim; and LFEC inspection of the entire zone.
Entry door: 20,000 .................
Service door: 40,000.
3,000
18,000
Entry door: 20,000 .................
Service door: 40,000.
3,000
3,000
HFEC rotary probe inspection of the aft zone (required only
for Group 1, Configuration 1, and only for the entry door).
Entry door: 20,000 .................
Service door: 40,000.
6,000
18,000
B ..............
1 Option
Grace period, in
flight cycles
Repetitive
interval, in flight
cycles
Option
A is mandatory for the forward entry door, upper and lower hinge cutouts, on Model 737–200C airplanes.
The service bulletin specifies
contacting Boeing for crack repair
instructions.
The service bulletin also states that
the service bulletin might in the future
be revised to include a preventive
modification that will eliminate the
need for the repetitive inspections. The
service bulletin specifies contacting
Boeing for information about this
modification.
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 below.
Difference Between the Proposed AD
and the Service Bulletin
The service bulletin specifies
contacting the manufacturer for
instructions for crack repair and for an
optional modification that would
terminate the repetitive inspections. But
this proposed AD would require doing
the repair and optional modification 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.
Costs of Compliance
There are about 2,437 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD, per
inspection cycle.
ESTIMATED COSTS
Average hourly labor rate
Cost per airplane
Number of
U.S.-registered
airplanes
13 to 14 .......................
mstockstill on PROD1PC66 with PROPOSALS
Work hours
$80
$1,040 to $1,120 .....................................
1,055
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,
VerDate Aug<31>2005
16:33 Oct 10, 2007
Jkt 214001
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,
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Fmt 4702
Sfmt 4702
Fleet cost
$1,097,200 to $1,181,600
‘‘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
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Federal Register / Vol. 72, No. 196 / Thursday, October 11, 2007 / Proposed Rules
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.
§ 39.13
[Amended]
mstockstill on PROD1PC66 with PROPOSALS
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2007–0024;
Directorate Identifier 2007–NM–086–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by November 26, 2007.
Affected ADs
(b) None.
VerDate Aug<31>2005
14:15 Oct 10, 2007
Jkt 214001
Applicability
(c) This AD applies to all Boeing Model
737–100, –200, –200C, –300, –400, and –500
series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from multiple reports
of cracks found in the skin, bearstrap, and/
or frame outer chord in the hinge cutout
areas of the forward entry and forward galley
service doorways. We are issuing this AD to
detect and correct such cracking, which
could 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) Except as provided by paragraph (g) of
this AD, at the applicable times specified in
paragraph 1.E. of Boeing Alert Service
Bulletin 737–53A1200, dated April 13, 2006,
do external detailed, low frequency eddy
current, high frequency eddy current, and
high frequency eddy current rotary probe
inspections, as applicable, for cracks in and
around the upper and lower hinge cutouts of
the forward entry and forward galley service
doorways, in accordance with the
Accomplishment Instructions of the service
bulletin, except as provided by paragraph (h)
of this AD. Do not exceed the applicable
repetitive interval for the previous
inspection, as specified in the service
bulletin as Option A or Option B. Repair any
crack before further flight using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
Exceptions to Service Bulletin Specifications
(g) Where the service bulletin specifies a
compliance time after the release date of the
service bulletin, this AD requires compliance
within the specified compliance time after
the effective date of this AD.
(h) Although the service bulletin specifies
contacting Boeing for information about
installing an optional preventive
modification that would terminate the
repetitive inspections specified in this AD,
this AD requires that any terminating action
be done by using a method approved in
accordance with the procedures specified in
paragraph (i) of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
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 the
approval must specifically refer to this AD.
Issued in Renton, Washington, on October
1, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–20048 Filed 10–10–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29329; Directorate
Identifier 2007–NM–205–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model 717–200 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain McDonnell Douglas Model 717–
200 airplanes. This proposed AD would
require modification of the conduit for
the forward boost pump of the center
fuel tank. This proposed AD results
from the finding that a potential chafing
condition exists in the volute assembly
of the forward boost pump for the center
fuel tank. We are proposing this AD to
prevent chafing of the forward boost
pump wiring that could lead to arcing
to the inside of the 45-degree angle
fitting, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
DATES: We must receive comments on
this proposed AD by November 26,
2007.
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.
• Governmentwide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
ADDRESSES:
E:\FR\FM\11OCP1.SGM
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]]>Agencies
[Federal Register Volume 72, Number 196 (Thursday, October 11, 2007)]
[Proposed Rules]
[Pages 57890-57892]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-20048]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0024; Directorate Identifier 2007-NM-086-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. This proposed AD would require repetitive inspections for
cracking in and around the upper and lower hinge cutouts of the forward
entry and forward galley service doorways, and corrective actions if
necessary. This proposed AD results from multiple reports of cracks
found in the skin, bearstrap, and/or frame outer chord in the hinge
cutout areas of the forward entry and forward galley service doorways.
We are proposing this AD to detect and correct such cracking, which
could result in rapid decompression of the airplane.
DATES: We must receive comments on this proposed AD by November 26,
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-
0024; Directorate Identifier 2007-NM-086-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 multiple reports of cracks found in the skin,
bearstrap, and/or frame outer chord in the hinge cutout areas of the
forward entry and forward galley service doorways. Cracks in the
forward entry door bearstrap were reported on an airplane with as few
as
[[Page 57891]]
24,538 total flight cycles. Cracks in the forward galley service door
bearstrap were reported on an airplane with as few as 44,938 total
flight cycles. One operator reported a severed bearstrap, a severed
station (STA) 291.5 frame, and a 14.5-inch crack in the skin at the
lower hinge cutout of the forward galley service doorway. The airplane
had accumulated 61,297 total flight cycles. Such cracking, if not
corrected, could result in rapid decompression of the airplane.
The fatigue cracks are caused by cyclic cabin pressure loads and
are not due to manufacturing defects in the bearstrap. The unsafe
condition is unrelated to any previous investigation related to
suspected unapproved parts.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-53A1200, dated
April 13, 2006. The service bulletin describes procedures for
repetitive inspections for cracking in and around the upper and lower
hinge cutouts of the forward entry and forward galley service doorways.
The service bulletin describes the following inspections:
External detailed inspection of the skin;
High frequency eddy current (HFEC) hole probe inspection
of the skin, bonded doubler, bearstrap, and frame chord at specified
fastener locations;
HFEC hole probe inspection of the skin, bonded doubler,
and bearstrap at specified fastener locations aft of the frame chord;
HFEC inspection of the skin hinge cutout trim;
Low frequency eddy current (LFEC) hole probe inspection of
the skin, bonded doubler, and bearstrap at specific fastener locations
aft of the frame chord;
LFEC hole probe inspection of the skin, bonded doubler,
bearstrap, and frame chord at specific fastener locations.
The service bulletin provides two options for the inspections, as
follows:
Compliance Times
----------------------------------------------------------------------------------------------------------------
Repetitive
Option Inspections Threshold, in total Grace period, in interval, in
flight cycles flight cycles flight cycles
----------------------------------------------------------------------------------------------------------------
A \1\................ External detailed Entry door: 20,000..... 3,000 18,000
inspection; HFEC inspection Service door: 40,000...
of the skin hinge cutout
trim; and HFEC rotary probe
inspection of the entire
zone.
B.................... External detailed Entry door: 20,000..... 3,000 3,000
inspection; HFEC inspection Service door: 40,000...
of the skin hinge cutout
trim; and LFEC inspection
of the entire zone.
����������������������
HFEC rotary probe inspection Entry door: 20,000..... 6,000 18,000
of the aft zone (required Service door: 40,000...
only for Group 1,
Configuration 1, and only
for the entry door).
----------------------------------------------------------------------------------------------------------------
\1\ Option A is mandatory for the forward entry door, upper and lower hinge cutouts, on Model 737-200C
airplanes.
The service bulletin specifies contacting Boeing for crack repair
instructions.
The service bulletin also states that the service bulletin might in
the future be revised to include a preventive modification that will
eliminate the need for the repetitive inspections. The service bulletin
specifies contacting Boeing for information about this modification.
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 below.
Difference Between the Proposed AD and the Service Bulletin
The service bulletin specifies contacting the manufacturer for
instructions for crack repair and for an optional modification that
would terminate the repetitive inspections. But this proposed AD would
require doing the repair and optional modification 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.
Costs of Compliance
There are about 2,437 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD, per inspection cycle.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Work hours Average hourly Cost per airplane registered Fleet cost
labor rate airplanes
----------------------------------------------------------------------------------------------------------------
13 to 14.......................... $80 $1,040 to $1,120.... 1,055 $1,097,200 to
$1,181,600
----------------------------------------------------------------------------------------------------------------
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
[[Page 57892]]
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-2007-0024; Directorate Identifier 2007-NM-
086-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by November
26, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from multiple reports of cracks found in the
skin, bearstrap, and/or frame outer chord in the hinge cutout areas
of the forward entry and forward galley service doorways. We are
issuing this AD to detect and correct such cracking, which could
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) Except as provided by paragraph (g) of this AD, at the
applicable times specified in paragraph 1.E. of Boeing Alert Service
Bulletin 737-53A1200, dated April 13, 2006, do external detailed,
low frequency eddy current, high frequency eddy current, and high
frequency eddy current rotary probe inspections, as applicable, for
cracks in and around the upper and lower hinge cutouts of the
forward entry and forward galley service doorways, in accordance
with the Accomplishment Instructions of the service bulletin, except
as provided by paragraph (h) of this AD. Do not exceed the
applicable repetitive interval for the previous inspection, as
specified in the service bulletin as Option A or Option B. Repair
any crack before further flight using a method approved in
accordance with the procedures specified in paragraph (i) of this
AD.
Exceptions to Service Bulletin Specifications
(g) Where the service bulletin specifies a compliance time after
the release date of the service bulletin, this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(h) Although the service bulletin specifies contacting Boeing
for information about installing an optional preventive modification
that would terminate the repetitive inspections specified in this
AD, this AD requires that any terminating action be done by using a
method approved in accordance with the procedures specified in
paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office (ACO),
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.
(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 the approval must specifically refer to this
AD.
Issued in Renton, Washington, on October 1, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-20048 Filed 10-10-07; 8:45 am]
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