Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes, 55118-55120 [E7-19205]
Download as PDF
55118
Federal Register / Vol. 72, No. 188 / Friday, September 28, 2007 / Proposed Rules
adaptors in accordance with the
Accomplishment instructions of APPH
Service Bulletin AIR83064–32–12, Revision
3, dated April 26, 2006; or AIR83022–32–32,
Revision 3, dated April 26, 2006; as
applicable.
(4) Actions done before the effective date
of this AD in accordance with the service
bulletins listed in paragraphs (f)(4)(i),
(f)(4)(ii), and (f)(4)(iii) of this AD, as
applicable, are acceptable for compliance
with the corresponding actions in this AD.
(i) Saab Service Bulletin 340–32–133,
dated April 19, 2006.
(ii) APPH Service Bulletin AIR 83064–32–
12, dated January 18, 2006; Revision 1, dated
January 23, 2006; and Revision 2, dated
March 30, 2006.
(iii) APPH Service Bulletin AIR83022–32–
32, dated January 18, 2006; Revision 1, dated
January 23, 2006; and Revision 2, dated
March 30, 2006.
(5) As of the effective date of this AD, no
person may install an MLG shock strut
having part number (P/N) AIR83022 or
83064, or axle adaptor having P/N
AIR127308, 390226, or AIR130238, unless it
has been inspected and modified in
accordance with APPH Service Bulletin
AIR83022–32–32 or AIR83064–32–12.
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, –800, and
–900 Series Airplanes
FAA AD Differences
AGENCY:
pwalker on PROD1PC71 with PROPOSALS
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, ANM–116,
International Branch, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Mike Borfitz,
Aerospace Engineer, International Branch,
ANM–116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2677; fax (425) 227–1149. 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.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2006–0263, dated August 29, 2006;
VerDate Aug<31>2005
17:39 Sep 27, 2007
Jkt 211001
Saab Service Bulletin 340–32–133, Revision
01, dated May 3, 2006; APPH Service
Bulletin AIR83064–32–12, Revision 3, dated
April 26, 2006; and APPH Service Bulletin
AIR83022–32–32, Revision 3, dated April 26,
2006; for related information.
Issued in Renton, Washington, on
September 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–19202 Filed 9–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29333; Directorate
Identifier 2007–NM–141–AD]
RIN 2120–AA64
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
certain Boeing Model 737–600, –700,
–700C, –800, and –900 series airplanes.
This proposed AD would require
various repetitive inspections to detect
cracks along the chemically milled steps
of the fuselage skin or missing or loose
fasteners in the area of the preventative
modification or repairs, replacement of
the time-limited repair with the
permanent repair if applicable, and
applicable corrective actions if
necessary, which would end certain
repetitive inspections. This proposed
AD results from a fatigue test that
revealed numerous cracks in the upper
skin panel at the chemically milled step
above the lap joint. We are proposing
this AD to detect and correct such
fatigue-related cracks, which could
result in the crack tips continuing to
turn and grow to the point where the
skin bay flaps open, causing
decompression of the airplane.
DATES: We must receive comments on
this proposed AD by November 13,
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.
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
• Governmentwide 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:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6447; 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–2007–29333; Directorate
Identifier 2007–NM–141–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
E:\FR\FM\28SEP1.SGM
28SEP1
Federal Register / Vol. 72, No. 188 / Friday, September 28, 2007 / Proposed Rules
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
We have received a report that, during
a fatigue test of the fuselage of a Boeing
Model 737–800 series airplane,
numerous cracks were found in the
upper skin panel at the chemically
milled step above the lap joint at
stringers 4 and 10 on both the left and
right sides of the airplane. The cracks
were caused by fatigue stresses
generated by secondary bending in the
lap splice. Such fatigue-related cracks, if
55119
not detected and corrected in a timely
manner, could result in the crack tips
continuing to turn and grow to the point
where the skin bay flaps open, causing
decompression of the airplane.
Relevant Service Information
We have reviewed Boeing Special
Attention Service Bulletin 737–53–
1232, dated April 2, 2007. The service
information describes the following
actions:
INSPECTIONS AND REPLACEMENT, AS APPLICABLE
For airplanes on which—
The service bulletin describes procedures for doing—
The preventative modification specified in the
service bulletin has not been installed.
The preventative modification specified in the
service bulletin has been installed.
An external eddy current inspection to detect cracks of the chemically milled steps at the
upper skin panels and repetitive external detailed inspections to detect cracks of the skin.
Repetitive external detailed inspections and repetitive external high frequency eddy current
(HFEC) inspections to detect cracks or loose or missing fasteners in the area of the preventative modification.
Repetitive external low frequency eddy current (LFEC) inspections to detect cracks in the skin.
The permanent repair specified in the service
bulletin has been installed.
pwalker on PROD1PC71 with PROPOSALS
The time-limited repair specified in the service
bulletin has been installed.
The service information also describes
procedures for doing applicable
corrective actions. The corrective
actions include contacting Boeing for
certain conditions, replacing any loose
or missing fastener with a new fastener,
and installing a permanent repair, timelimited repair, and preventative
modification. For airplanes on which
the preventative modification has not
been installed, accomplishing the
preventative modification, time-limited
repair, or permanent repair ends the
repetitive external detailed inspections
only.
The service information also specifies
the following compliance times:
• For the initial inspections and
replacement: Compliance times ranging
between 1,500 flight cycles and 56,000
total flight cycles, depending on the
airplane configuration and the
inspection method.
• For the applicable corrective
actions: A compliance time of before
further flight.
• For repetitive inspections: Repeat
intervals ranging between 1,100 and
8,000 flight cycles, depending on the
airplane configuration.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
VerDate Aug<31>2005
17:39 Sep 27, 2007
Jkt 211001
Repetitive external LFEC inspections to detect cracks of the doubler.
Repetitive external detailed inspections to detect cracks or loose or missing fasteners of the
permanent repair.
Repetitive internal medium frequency eddy current inspections to detect cracks of the skin if
doing ‘‘Skin Inspection Option 2’’ specified in Table 2 of the service bulletin
Repetitive internal and external detailed inspections to detect cracks or loose or missing fasteners of the repaired area and replacement of the time-limited repair with the permanent repair.
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
‘‘Difference Between the Proposed AD
and Service Information.’’
Difference Between the Proposed AD
and Service Information
The service information 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.
Costs of Compliance
There are about 871 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
378 airplanes of U.S. registry. The
proposed inspections would take
between 11 and 25 work hours per
airplane depending on the airplane
configuration, 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
between $332,640 and $756,000, or
between $880 and $2,000 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.
E:\FR\FM\28SEP1.SGM
28SEP1
55120
Federal Register / Vol. 72, No. 188 / Friday, September 28, 2007 / Proposed Rules
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]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2007–29333;
Directorate Identifier 2007–NM–141–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by November 13, 2007.
pwalker on PROD1PC71 with PROPOSALS
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 Special Attention
Service Bulletin 737–53–1232, dated April 2,
2007.
VerDate Aug<31>2005
17:39 Sep 27, 2007
Jkt 211001
Unsafe Condition
(d) This AD results from a fatigue test that
revealed numerous cracks in the upper skin
panel at the chemically milled step above the
lap joint. We are issuing this AD to detect
and correct such fatigue-related cracks,
which could result in the crack tips
continuing to turn and grow to the point
where the skin bay flaps open, causing
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.
Service Bulletin
(f) The term ‘‘service bulletin,’’ as used in
this AD, means Boeing Special Attention
Service Bulletin 737–53–1232, dated April 2,
2007.
Inspections and Replacement, as Applicable
(g) At the applicable compliance times
listed in Tables 1, 2, and 3 of paragraph 1.E.,
‘‘Compliance,’’ of the service bulletin, or
within the time specified in paragraph (g)(1)
or (g)(2) of this AD, as applicable, whichever
occurs later, and thereafter at the applicable
repeat intervals listed in Tables 1, 2, and 3:
Do the applicable inspections and
replacement by accomplishing all the actions
specified in the Accomplishment
Instructions of the service bulletin.
(1) For airplanes specified in Tables 1 and
2 of paragraph 1.E., ‘‘Compliance,’’ of the
service bulletin: Do the applicable initial
inspection required by paragraph (g) of this
AD within 36 months after the effective date
of this AD.
(2) For airplanes specified in Table 3 of
paragraph 1.E., ‘‘Compliance,’’ of the service
bulletin: Do the applicable initial inspection
and replacement required by paragraph (g) of
this AD within 24 months after the effective
date of this AD.
Corrective Actions
(h) If any crack or loose or missing fastener
is found during any applicable inspection
required by paragraph (g) of this AD, before
further flight, do the applicable corrective
action in accordance with the service
bulletin; except, where the service bulletin
specifies to contact Boeing for appropriate
action, before further flight, repair the crack
using a method approved in accordance with
the procedures specified in paragraph (j) of
this AD.
Terminating Action for Certain Repetitive
Inspections
(i) For airplanes on which the preventative
modification specified in the service bulletin
has not been installed: Accomplishing the
preventative modification, time-limited
repair, or permanent repair in accordance
with the service bulletin ends the applicable
repetitive external detailed inspections
required by paragraph (g) of this AD.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
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
September 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–19205 Filed 9–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29176; Directorate
Identifier 2007–NE–38–AD]
RIN 2120–AA64
Airworthiness Directives; McCauley
Propeller Systems Model 4HFR34C653/
L106FA Propellers
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
McCauley Propeller Systems model
4HFR34C653/L106FA propellers. This
proposed AD would require a onetime
fluorescent penetrant inspection (FPI)
and eddy current inspection (ECI) of the
propeller hub for cracks. This proposed
AD results from reports of 3 hubs found
cracked during propeller overhaul. We
are proposing this AD to prevent failure
of the propeller hub, which could cause
blade separation, damage to the
airplane, and loss of control of the
airplane.
We must receive any comments
on this proposed AD by November 27,
2007.
DATES:
E:\FR\FM\28SEP1.SGM
28SEP1
Agencies
[Federal Register Volume 72, Number 188 (Friday, September 28, 2007)]
[Proposed Rules]
[Pages 55118-55120]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-19205]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29333; Directorate Identifier 2007-NM-141-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).
-----------------------------------------------------------------------
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 various repetitive
inspections to detect cracks along the chemically milled steps of the
fuselage skin or missing or loose fasteners in the area of the
preventative modification or repairs, replacement of the time-limited
repair with the permanent repair if applicable, and applicable
corrective actions if necessary, which would end certain repetitive
inspections. This proposed AD results from a fatigue test that revealed
numerous cracks in the upper skin panel at the chemically milled step
above the lap joint. We are proposing this AD to detect and correct
such fatigue-related cracks, which could result in the crack tips
continuing to turn and grow to the point where the skin bay flaps open,
causing decompression of the airplane.
DATES: We must receive comments on this proposed AD by November 13,
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.
Governmentwide 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: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6447; 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-
29333; Directorate Identifier 2007-NM-141-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
[[Page 55119]]
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
We have received a report that, during a fatigue test of the
fuselage of a Boeing Model 737-800 series airplane, numerous cracks
were found in the upper skin panel at the chemically milled step above
the lap joint at stringers 4 and 10 on both the left and right sides of
the airplane. The cracks were caused by fatigue stresses generated by
secondary bending in the lap splice. Such fatigue-related cracks, if
not detected and corrected in a timely manner, could result in the
crack tips continuing to turn and grow to the point where the skin bay
flaps open, causing decompression of the airplane.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 737-53-
1232, dated April 2, 2007. The service information describes the
following actions:
Inspections and Replacement, as Applicable
------------------------------------------------------------------------
The service bulletin describes procedures
For airplanes on which-- for doing--
------------------------------------------------------------------------
The preventative modification An external eddy current inspection to
specified in the service detect cracks of the chemically milled
bulletin has not been steps at the upper skin panels and
installed. repetitive external detailed inspections
to detect cracks of the skin.
The preventative modification Repetitive external detailed inspections
specified in the service and repetitive external high frequency
bulletin has been installed. eddy current (HFEC) inspections to
detect cracks or loose or missing
fasteners in the area of the
preventative modification.
The permanent repair Repetitive external low frequency eddy
specified in the service current (LFEC) inspections to detect
bulletin has been installed. cracks in the skin.
Repetitive external LFEC inspections to
detect cracks of the doubler.
Repetitive external detailed inspections
to detect cracks or loose or missing
fasteners of the permanent repair.
Repetitive internal medium frequency eddy
current inspections to detect cracks of
the skin if doing ``Skin Inspection
Option 2'' specified in Table 2 of the
service bulletin
The time-limited repair Repetitive internal and external detailed
specified in the service inspections to detect cracks or loose or
bulletin has been installed. missing fasteners of the repaired area
and replacement of the time-limited
repair with the permanent repair.
------------------------------------------------------------------------
The service information also describes procedures for doing
applicable corrective actions. The corrective actions include
contacting Boeing for certain conditions, replacing any loose or
missing fastener with a new fastener, and installing a permanent
repair, time-limited repair, and preventative modification. For
airplanes on which the preventative modification has not been
installed, accomplishing the preventative modification, time-limited
repair, or permanent repair ends the repetitive external detailed
inspections only.
The service information also specifies the following compliance
times:
For the initial inspections and replacement: Compliance
times ranging between 1,500 flight cycles and 56,000 total flight
cycles, depending on the airplane configuration and the inspection
method.
For the applicable corrective actions: A compliance time
of before further flight.
For repetitive inspections: Repeat intervals ranging
between 1,100 and 8,000 flight cycles, depending on the airplane
configuration.
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
``Difference Between the Proposed AD and Service Information.''
Difference Between the Proposed AD and Service Information
The service information 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.
Costs of Compliance
There are about 871 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 378 airplanes of
U.S. registry. The proposed inspections would take between 11 and 25
work hours per airplane depending on the airplane configuration, 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 between
$332,640 and $756,000, or between $880 and $2,000 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.
[[Page 55120]]
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-2007-29333; Directorate Identifier 2007-NM-
141-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by November
13, 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 Special Attention Service Bulletin 737-53-1232,
dated April 2, 2007.
Unsafe Condition
(d) This AD results from a fatigue test that revealed numerous
cracks in the upper skin panel at the chemically milled step above
the lap joint. We are issuing this AD to detect and correct such
fatigue-related cracks, which could result in the crack tips
continuing to turn and grow to the point where the skin bay flaps
open, causing 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.
Service Bulletin
(f) The term ``service bulletin,'' as used in this AD, means
Boeing Special Attention Service Bulletin 737-53-1232, dated April
2, 2007.
Inspections and Replacement, as Applicable
(g) At the applicable compliance times listed in Tables 1, 2,
and 3 of paragraph 1.E., ``Compliance,'' of the service bulletin, or
within the time specified in paragraph (g)(1) or (g)(2) of this AD,
as applicable, whichever occurs later, and thereafter at the
applicable repeat intervals listed in Tables 1, 2, and 3: Do the
applicable inspections and replacement by accomplishing all the
actions specified in the Accomplishment Instructions of the service
bulletin.
(1) For airplanes specified in Tables 1 and 2 of paragraph 1.E.,
``Compliance,'' of the service bulletin: Do the applicable initial
inspection required by paragraph (g) of this AD within 36 months
after the effective date of this AD.
(2) For airplanes specified in Table 3 of paragraph 1.E.,
``Compliance,'' of the service bulletin: Do the applicable initial
inspection and replacement required by paragraph (g) of this AD
within 24 months after the effective date of this AD.
Corrective Actions
(h) If any crack or loose or missing fastener is found during
any applicable inspection required by paragraph (g) of this AD,
before further flight, do the applicable corrective action in
accordance with the service bulletin; except, where the service
bulletin specifies to contact Boeing for appropriate action, before
further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (j) of this
AD.
Terminating Action for Certain Repetitive Inspections
(i) For airplanes on which the preventative modification
specified in the service bulletin has not been installed:
Accomplishing the preventative modification, time-limited repair, or
permanent repair in accordance with the service bulletin ends the
applicable repetitive external detailed inspections required by
paragraph (g) of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(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 September 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-19205 Filed 9-27-07; 8:45 am]
BILLING CODE 4910-13-P