Airworthiness Directives; Boeing Model 747-100, -200B, -200C, and -200F Series Airplanes, 29084-29086 [E7-10045]
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29084
Federal Register / Vol. 72, No. 100 / Thursday, May 24, 2007 / Proposed Rules
fitted with resistor manufactured by SRT
until accomplishment of terminating action
(installation of BCM fitted with resistors
manufactured by VISHAY).
The unsafe condition is erratic motion of the
rudder and could result in reduced
controllability of the airplane due to dutch
roll characteristics.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 900 flight hours after the
effective date of this AD, and thereafter at
intervals not to exceed 900 flight hours,
perform an operational test of the BCM and
back-up power supply (BPS) by BITE (built
in test equipment), and as applicable, apply
the corrective actions, in accordance with
instructions defined in Airbus Service
Bulletin A330–27–3147, dated August 4,
2006; Airbus Service Bulletin A340–27–4147,
dated August 4, 2006; or Airbus Service
Bulletin A340–27–5038, dated August 4,
2006; as applicable. Replacement of affected
BCM in accordance with Airbus Service
Bulletin A330–27–3142, dated August 17,
2006; A340–27–4142, dated August 17, 2006;
or A340–27–5036, dated August 17, 2006;
cancels the mandatory repetitive operational
test.
(2) Within 26 months after the effective
date of this AD, install modified BCM in
accordance with instructions given in Airbus
Service Bulletin A330–27–3142, dated
August 17, 2006; Airbus Service Bulletin
A340–27–4142, dated August 17, 2006; or
Airbus Service Bulletin A340–27–5036,
dated August 17, 2006; as applicable.
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2006–
0313, dated October 13, 2006; and the service
bulletins listed in Table 1 for related
information.
TABLE 1.—AIRBUS SERVICE BULLETINS
Airbus Service
Bulletin—
Dated—
A330–27–3123 ...........
A330–27–3142 ...........
A330–27–3147, including Appendix 01.
A340–27–4124 ...........
A340–27–4142 ...........
A340–27–4147, including Appendix 01.
A340–27–5036 ...........
A340–27–5038, including Appendix 01.
December 13, 2004.
August 17, 2006.
August 4, 2006.
December 13, 2004.
August 17, 2006.
August 4, 2006.
August 17, 2006.
August 4, 2006.
Issued in Renton, Washington, on May 15,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10043 Filed 5–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Note: This AD differs from the MCAI and/
or service information as follows: No
Differences.
rmajette on PROD1PC67 with PROPOSALS
FAA AD Differences
14 CFR Part 39
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tim Backman,
Aerospace Engineer; 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–2797; fax (425) 227–1149. Before
using any AMOC approved in accordance
with § 39.19 on any airplane to which the
AMOC applies, notify the appropriate
principal inspector in the FAA Flight
Standards Certificate Holding District Office.
(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
VerDate Aug<31>2005
15:42 May 23, 2007
Jkt 211001
[Docket No. FAA–2007–28257; Directorate
Identifier 2007–NM–034–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, –200B, –200C, and
–200F 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
certain Boeing Model 747–100, –200B,
–200C, and –200F series airplanes. This
proposed AD would require performing
repetitive inspections for cracks in the
fuselage skin at the cutout of the bulk
cargo door light, and corrective actions
if necessary. This proposed AD also
provides terminating action for
airplanes with a certain type of damage.
This proposed AD results from a report
of a 2-inch crack through the fuselage
skin and internal bonded doubler at the
cutout of the bulk cargo door light. We
are proposing this AD to detect and
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
correct cracks in the fuselage skin at the
cutout of the bulk cargo door light,
which could result in reduced structural
integrity of the fuselage at the bulk cargo
door and consequent rapid
decompression of the fuselage.
DATES: We must receive comments on
this proposed AD by July 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: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., 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: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6437;
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–2007–28257; Directorate
Identifier 2007–NM–034–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
E:\FR\FM\24MYP1.SGM
24MYP1
Federal Register / Vol. 72, No. 100 / Thursday, May 24, 2007 / Proposed Rules
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 Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif 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.
rmajette on PROD1PC67 with PROPOSALS
Discussion
We have received a report indicating
that a 2-inch crack through the fuselage
skin and internal bonded doubler at the
cutout of the bulk cargo door light was
found during a visual fuselage skin
inspection on a Model 747–200F series
airplane. The crack was located at the
forward lower corner of the cutout of
the bulk cargo door light between
stations 2060 and 2070, stringers 32R
and 33R. The airplane had accumulated
approximately 24,613 flight cycles and
99,339 flight hours. This condition, if
not corrected, could result in reduced
structural integrity of the fuselage at the
bulk cargo door and consequent rapid
decompression of the fuselage.
The subject area on certain Model
747–100, 200B, and –200C series
airplanes is almost identical to that on
the affected Model 747–200F series
airplanes. Therefore, those airplanes are
subject to the unsafe condition revealed
on the Model 747–200F series airplane.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 747–53A2673, dated
February 8, 2007. The service bulletin
describes procedures for repetitive high
frequency eddy current (HFEC)
inspections for cracks in the fuselage
skin at the cutout of the bulk cargo door
light, and corrective actions if
necessary. The corrective actions are as
follows:
• For airplanes on which a crack is
found that is 2.0 inches or less in length
from the edge of the light cutout forward
lower corner, Part 2 of the
Accomplishment Instructions of the
service bulletin describes procedures for
VerDate Aug<31>2005
15:42 May 23, 2007
Jkt 211001
installing a repair filler, doubler, and
tripler, and performing an additional
HFEC inspection of the trim edge for
cracks and repairing any crack.
Accomplishing these corrective actions
eliminates the need for the repetitive
inspections.
• For airplanes on which a crack is
found that is more than 2.0 inches in
total length from the edge of the light
cutout forward lower corner, or is at a
location other than the light cutout
forward lower corner, the service
bulletin recommends contacting Boeing
for repair instructions and doing the
repair.
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 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.
29085
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.
Costs of Compliance
There are about 65 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about 36
airplanes of U.S. registry. The proposed
actions would take about 2 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
$5,760, or $160 per airplane, per
inspection cycle.
List of Subjects in 14 CFR Part 39
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
1. The authority citation for part 39
continues to read as follows:
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Frm 00004
Fmt 4702
Sfmt 4702
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
Authority: 49 U.S.C. 106(g), 40113, 44701.
E:\FR\FM\24MYP1.SGM
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29086
§ 39.13
Federal Register / Vol. 72, No. 100 / Thursday, May 24, 2007 / Proposed Rules
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2007–28257;
Directorate Identifier 2007–NM–034–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by July 9, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
100, –200B, –200C, and –200F series
airplanes, certificated in any category; as
identified in Boeing Alert Service Bulletin
747–53A2673, dated February 8, 2007.
Unsafe Condition
(d) This AD results from a report of a 2inch crack through the fuselage skin and
internal bonded doubler at the cutout of the
bulk cargo door light. We are issuing this AD
to detect and correct cracks in the fuselage
skin at the cutout of the bulk cargo door light,
which could result in reduced structural
integrity of the fuselage at the bulk cargo
door and consequent rapid decompression of
the fuselage.
rmajette on PROD1PC67 with PROPOSALS
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.
Inspections/Corrective Actions
(f) Before the accumulation of 20,000 total
flight cycles, or within 1,500 flight cycles
after the effective date of this AD, whichever
is later: Perform a high frequency eddy
current (HFEC) inspection for cracks in the
fuselage skin at the cutout of the bulk cargo
door light, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2673, dated
February 8, 2007. Repeat the inspection
thereafter at intervals not to exceed 3,000
flight cycles.
(1) If no crack is found: Repeat the
inspection required by paragraph (f) of this
AD at the time specified.
(2) If any crack is found that is 2.0 inches
or less in length from the edge of the light
cutout forward lower corner: Before further
flight, do all the corrective actions (including
an additional HFEC inspection for cracks) in
accordance with Part 2 of the
Accomplishment Instructions of the service
bulletin. Accomplishing Part 2 ends the
repetitive inspections required by paragraph
(f) of this AD.
(3) If any crack is found during the
inspection required by paragraph (f) of this
AD that is more than 2.0 inches in total
length from the edge of the light cutout
forward lower corner, or is at a location other
than the light cutout forward lower corner:
Before further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (g)(2) of this AD.
VerDate Aug<31>2005
15:42 May 23, 2007
Jkt 211001
Alternative Methods of Compliance
(AMOCs)
(g)(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) 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.
(3) 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 May 15,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10045 Filed 5–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28259; Directorate
Identifier 2007–NM–024–AD]
RIN 2120–AA64
Airworthiness Directives; Aerospatiale
Model SN–601 (Corvette) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
SUMMARY:
Cracks have been evidenced on the nose
landing gear LH (left-hand) and RH (righthand) hinge fittings due to stress corrosion
on in-service aircraft. If undetected, they
could lead to complete rupture of one or two
of the fittings.
The unsafe condition is collapse of the
nose landing gear. The proposed AD
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
would require actions that are intended
to address the unsafe condition
described in the MCAI.
DATES: We must receive comments on
this proposed AD by June 25, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
proposed AD, the regulatory evaluation,
any comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
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.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
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]]>Agencies
[Federal Register Volume 72, Number 100 (Thursday, May 24, 2007)]
[Proposed Rules]
[Pages 29084-29086]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10045]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28257; Directorate Identifier 2007-NM-034-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, -200B, -200C, and
-200F 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 747-100, -200B, -200C, and -200F series
airplanes. This proposed AD would require performing repetitive
inspections for cracks in the fuselage skin at the cutout of the bulk
cargo door light, and corrective actions if necessary. This proposed AD
also provides terminating action for airplanes with a certain type of
damage. This proposed AD results from a report of a 2-inch crack
through the fuselage skin and internal bonded doubler at the cutout of
the bulk cargo door light. We are proposing this AD to detect and
correct cracks in the fuselage skin at the cutout of the bulk cargo
door light, which could result in reduced structural integrity of the
fuselage at the bulk cargo door and consequent rapid decompression of
the fuselage.
DATES: We must receive comments on this proposed AD by July 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: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., 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: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437;
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-
28257; Directorate Identifier 2007-NM-034-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
[[Page 29085]]
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 Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif 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 a 2-inch crack through
the fuselage skin and internal bonded doubler at the cutout of the bulk
cargo door light was found during a visual fuselage skin inspection on
a Model 747-200F series airplane. The crack was located at the forward
lower corner of the cutout of the bulk cargo door light between
stations 2060 and 2070, stringers 32R and 33R. The airplane had
accumulated approximately 24,613 flight cycles and 99,339 flight hours.
This condition, if not corrected, could result in reduced structural
integrity of the fuselage at the bulk cargo door and consequent rapid
decompression of the fuselage.
The subject area on certain Model 747-100, 200B, and -200C series
airplanes is almost identical to that on the affected Model 747-200F
series airplanes. Therefore, those airplanes are subject to the unsafe
condition revealed on the Model 747-200F series airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-53A2673, dated
February 8, 2007. The service bulletin describes procedures for
repetitive high frequency eddy current (HFEC) inspections for cracks in
the fuselage skin at the cutout of the bulk cargo door light, and
corrective actions if necessary. The corrective actions are as follows:
For airplanes on which a crack is found that is 2.0 inches
or less in length from the edge of the light cutout forward lower
corner, Part 2 of the Accomplishment Instructions of the service
bulletin describes procedures for installing a repair filler, doubler,
and tripler, and performing an additional HFEC inspection of the trim
edge for cracks and repairing any crack. Accomplishing these corrective
actions eliminates the need for the repetitive inspections.
For airplanes on which a crack is found that is more than
2.0 inches in total length from the edge of the light cutout forward
lower corner, or is at a location other than the light cutout forward
lower corner, the service bulletin recommends contacting Boeing for
repair instructions and doing the repair.
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 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.
Costs of Compliance
There are about 65 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 36 airplanes of
U.S. registry. The proposed actions would take about 2 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
$5,760, or $160 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.
[[Page 29086]]
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-2007-28257; Directorate Identifier 2007-NM-
034-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by July 9,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-100, -200B, -200C, and -
200F series airplanes, certificated in any category; as identified
in Boeing Alert Service Bulletin 747-53A2673, dated February 8,
2007.
Unsafe Condition
(d) This AD results from a report of a 2-inch crack through the
fuselage skin and internal bonded doubler at the cutout of the bulk
cargo door light. We are issuing this AD to detect and correct
cracks in the fuselage skin at the cutout of the bulk cargo door
light, which could result in reduced structural integrity of the
fuselage at the bulk cargo door and consequent rapid decompression
of the fuselage.
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.
Inspections/Corrective Actions
(f) Before the accumulation of 20,000 total flight cycles, or
within 1,500 flight cycles after the effective date of this AD,
whichever is later: Perform a high frequency eddy current (HFEC)
inspection for cracks in the fuselage skin at the cutout of the bulk
cargo door light, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-53A2673, dated February 8,
2007. Repeat the inspection thereafter at intervals not to exceed
3,000 flight cycles.
(1) If no crack is found: Repeat the inspection required by
paragraph (f) of this AD at the time specified.
(2) If any crack is found that is 2.0 inches or less in length
from the edge of the light cutout forward lower corner: Before
further flight, do all the corrective actions (including an
additional HFEC inspection for cracks) in accordance with Part 2 of
the Accomplishment Instructions of the service bulletin.
Accomplishing Part 2 ends the repetitive inspections required by
paragraph (f) of this AD.
(3) If any crack is found during the inspection required by
paragraph (f) of this AD that is more than 2.0 inches in total
length from the edge of the light cutout forward lower corner, or is
at a location other than the light cutout forward lower corner:
Before further flight, repair using a method approved in accordance
with the procedures specified in paragraph (g)(2) of this AD.
Alternative Methods of Compliance (AMOCs)
(g)(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) 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.
(3) 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 May 15, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-10045 Filed 5-23-07; 8:45 am]
BILLING CODE 4910-13-P
