Airworthiness Directives; Boeing Model 747-200C and 747-200F Series Airplanes, 14587-14589 [05-5695]
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Federal Register / Vol. 70, No. 55 / Wednesday, March 23, 2005 / Proposed Rules
proposed AD for U.S. operators is
$1,495, or $65 per airplane.
PART 39—AIRWORTHINESS
DIRECTIVES
Authority for This Rulemaking
1. The authority citation for part 39
continues to read as follows:
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. 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:
VerDate jul<14>2003
16:19 Mar 22, 2005
Jkt 205001
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2005–20691;
Directorate Identifier 2004–NM–249–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this AD
action by May 9, 2005.
14587
after the effective date of this AD, whichever
occurs later, submit a report of any positive
inspection results (P/N and S/N of the
reaction link match those listed in the Boeing
Service Bulletins) to the Manager, Seattle
Aircraft Certification Office (ACO), FAA,
1601 Lind Avenue, SW., Renton,
Washington. Include the P/N and S/N of the
affected reaction link, and the S/N of the
airplane on which the reaction link was
found, in the report. Information collection
requirements contained in this AD have been
approved by the Office of Management and
Budget (OMB) under the provisions of the
Paperwork Reduction Act of 1980 (44 U.S.C.
3501 et seq.) and have been assigned OMB
Control Number 2120–0056.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 757–
200 and –300 series airplanes, certificated in
any category; as identified in the Effectivity
of Boeing Service Bulletin 757–32–0155 and
757–32–0156, both dated September 30,
2004, as applicable.
Parts Installation
(h) As of the effective date of this AD, no
person may install a reaction link with a P/
N and S/N listed in the service bulletin that
is not marked ‘‘RETESTED,’’ on any airplane.
Alternative Methods of Compliance
(AMOCs)
(i) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
Unsafe Condition
(d) This AD was prompted by a report of
faulty welds in certain reaction links on main
landing gears (MLG). We are issuing this AD
to prevent failure of the reaction link,
collapse of the MLG, and consequently, loss
of control on the ground and possible damage
to 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.
Inspection and Corrective Action
(f) Within 12 months after the effective
date of this AD, inspect for the part number
(P/N), the serial number (S/N), and the
presence of the mark ‘‘RETESTED’’ on the
reaction link of the MLG in accordance with
the Accomplishment Instructions of Boeing
Service Bulletin 757–32–0155 or 757–32–
0156, both dated September 30, 2004, as
applicable.
(1) If the P/N and S/N do not match any
P/N and S/N listed in Appendix A of the
applicable service bulletin, or if the reaction
link is marked ‘‘RETESTED,’’ no further
action is required by this paragraph.
(2) If the P/N and S/N match those listed
in Appendix A of the applicable service
bulletin, and the reaction link is not marked
‘‘RETESTED,’’ before further flight, replace
the reaction link with a retested reaction link
in accordance with the Accomplishment
Instructions of the service bulletin and
perform the requirement of paragraph (g) of
this AD at the time specified in paragraph (g).
Inspection Report
(g) For any reaction link with a P/N and
S/N listed in the service bulletin that is or
is not marked ‘‘RETESTED’’: Within 30 days
after accomplishing the inspection required
by paragraph (f) of this AD or within 30 days
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Frm 00010
Fmt 4702
Sfmt 4702
Issued in Renton, Washington, on March
14, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–5694 Filed 3–22–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20690; Directorate
Identifier 2003–NM–230–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–200C and 747–200F 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 747–200C and
747–200F series airplanes. This
proposed AD would require one-time
inspections for cracks and material loss
in the fuselage skin above the stringer
(STR) 23 lap splice, between Body
Station (BS) 282 and BS 298, and repair
if necessary. This proposed AD is
prompted by a report of a crack above
the STR 23 lap splice on one airplane.
We are proposing this AD to detect and
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14588
Federal Register / Vol. 70, No. 55 / Wednesday, March 23, 2005 / Proposed Rules
correct cracks or material loss in the
fuselage skin, and consequent reduced
structural integrity of the skin panel,
which could result in rapid
depressurization of the airplane.
DATES: We must receive comments on
this proposed AD by May 9, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to http:/
/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.
• By 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.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20690; the directorate identifier for this
docket is 2003–NM–230–AD.
FOR FURTHER INFORMATION CONTACT: Nick
Kusz, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6432;
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 under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20690; Directorate Identifier
2003–NM–230–AD’’ in the subject line
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
VerDate jul<14>2003
16:19 Mar 22, 2005
Jkt 205001
submitted 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 can
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Relevant Service Information
Examining the Docket
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. Therefore, we are
proposing this AD, which accomplishes
the actions specified in the service
information described previously,
except as discussed under ‘‘Difference
Between the Proposed AD and the
Service Bulletin.’’
You can 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 DMS
receives them.
Discussion
We have received a report of a 3-inch
skin crack on a Boeing Model 747–200F
series airplane. The crack was located
immediately above the Stringer (STR) 23
lap splice, between Body Station (BS)
282 and BS 298. The crack started in an
area of the skin that had been
inadvertently damaged during
manufacture when an internal skin
doubler was trimmed by grinding. The
crack propagated by fatigue from the
reworked area. This condition, if not
corrected, could result in cracks in the
fuselage skin, and consequent reduced
structural integrity of the skin panel,
which could cause rapid
depressurization of the airplane.
The subject area on Boeing Model
747–200C series airplanes that are
equipped with a nose cargo door is
almost identical to that on Boeing
Model 747–200F series airplanes that
are equipped with a nose cargo door.
Therefore, Boeing Model 747–200C
series airplanes may be subject to the
same unsafe condition.
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Frm 00011
Fmt 4702
Sfmt 4702
We have reviewed Boeing Special
Attention Service Bulletin 747–53–
2493, dated July 3, 2003. The service
bulletin describes procedures for doing
a one-time external detailed visual
inspection for cracks, and a one-time
low frequency eddy current inspection
for material loss. The area to be
inspected is 3.2 inches to 4.3 inches
above the lower edge of the upper skin
at STR 23L and STR 23R, from BS 282
to BS 298. If cracks are found, or if the
skin is less than 0.056 inch thick, the
service bulletin describes procedures for
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
Difference Between the Proposed AD
and the Service Bulletin
The ‘‘Effectivity’’ paragraph in Boeing
Special Attention Service Bulletin 747–
53–2493, dated July 3, 2003, states that
the service bulletin applies to all Boeing
Model 747–200C and all Boeing Model
747–200F series airplanes. However,
there was an unintended omission in
the service bulletin. This proposed AD
would apply only to Boeing Model 747–
200C and Boeing Model 747–200F series
airplanes that are equipped with a nose
cargo door. This difference has been
coordinated with the manufacturer.
Clarification of Inspection Language
The service bulletin refers to a
detailed visual inspection. However,
this proposed AD refers to this
inspection as a ‘‘detailed inspection.’’
Note 1 of this proposed AD defines a
detailed inspection.
Costs of Compliance
There are about 77 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.
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Federal Register / Vol. 70, No. 55 / Wednesday, March 23, 2005 / Proposed Rules
ESTIMATED COSTS
Action
Work hour
Average
labor rate
per hour
Parts
Cost per
airplane
Number of
U.S.-registered
airplanes
Fleet
cost
Inspections ...............................................
6
$65
None
$390
20
$7,800
Authority for This Rulemaking
The Proposed Amendment
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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. 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.
VerDate jul<14>2003
16:19 Mar 22, 2005
Jkt 205001
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Affected ADs
(b) None.
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
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.
Applicability
(c) This AD applies to Boeing Model 747–
200C and 747–200F series airplanes,
equipped with a nose cargo door, certificated
in any category; as identified in paragraph
1.A.1 of Boeing Special Attention Service
Bulletin 747–53–2493, dated July 3, 2003.
Issued in Renton, Washington, on March
14, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–5695 Filed 3–22–05; 8:45 am]
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2005–20690;
Directorate Identifier 2003–NM–230–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this AD
action by May 9, 2005.
Unsafe Condition
(d) This AD was prompted by a report of
a crack above the stringer (STR) 23 lap splice
on a 747–200F series airplane. We are issuing
this AD to detect and correct cracks or
material loss in the fuselage skin, and
consequent reduced structural integrity of the
skin panel, which could result in rapid
depressurization 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.
Inspections and Repair
(f) Before the accumulation of 15,000 total
flight cycles, or within 1,200 flight cycles
after the effective date of this AD, whichever
occurs later: Do a detailed inspection for
cracking, and a low frequency eddy current
inspection for material loss, in the fuselage
skin. Repair any crack or material loss prior
to further flight. Do all actions in accordance
with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
747–53–2493, dated July 3, 2003.
PO 00000
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Fmt 4702
Sfmt 4702
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20692; Directorate
Identifier 2004–NM–229–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–200F,
747–300, 747SR, and 747SP 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
E:\FR\FM\23MRP1.SGM
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]]>Agencies
[Federal Register Volume 70, Number 55 (Wednesday, March 23, 2005)]
[Proposed Rules]
[Pages 14587-14589]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-5695]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20690; Directorate Identifier 2003-NM-230-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-200C and 747-200F
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 747-200C and 747-200F series airplanes. This
proposed AD would require one-time inspections for cracks and material
loss in the fuselage skin above the stringer (STR) 23 lap splice,
between Body Station (BS) 282 and BS 298, and repair if necessary. This
proposed AD is prompted by a report of a crack above the STR 23 lap
splice on one airplane. We are proposing this AD to detect and
[[Page 14588]]
correct cracks or material loss in the fuselage skin, and consequent
reduced structural integrity of the skin panel, which could result in
rapid depressurization of the airplane.
DATES: We must receive comments on this proposed AD by May 9, 2005.
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.
By 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.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street, SW., room PL-
401, on the plaza level of the Nassif Building, Washington, DC. This
docket number is FAA-2005-20690; the directorate identifier for this
docket is 2003-NM-230-AD.
FOR FURTHER INFORMATION CONTACT: Nick Kusz, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6432; 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 under ADDRESSES. Include ``Docket No. FAA-2005-20690;
Directorate Identifier 2003-NM-230-AD'' in the subject line 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 submitted 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 can review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
You can 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 DMS receives them.
Discussion
We have received a report of a 3-inch skin crack on a Boeing Model
747-200F series airplane. The crack was located immediately above the
Stringer (STR) 23 lap splice, between Body Station (BS) 282 and BS 298.
The crack started in an area of the skin that had been inadvertently
damaged during manufacture when an internal skin doubler was trimmed by
grinding. The crack propagated by fatigue from the reworked area. This
condition, if not corrected, could result in cracks in the fuselage
skin, and consequent reduced structural integrity of the skin panel,
which could cause rapid depressurization of the airplane.
The subject area on Boeing Model 747-200C series airplanes that are
equipped with a nose cargo door is almost identical to that on Boeing
Model 747-200F series airplanes that are equipped with a nose cargo
door. Therefore, Boeing Model 747-200C series airplanes may be subject
to the same unsafe condition.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 747-53-
2493, dated July 3, 2003. The service bulletin describes procedures for
doing a one-time external detailed visual inspection for cracks, and a
one-time low frequency eddy current inspection for material loss. The
area to be inspected is 3.2 inches to 4.3 inches above the lower edge
of the upper skin at STR 23L and STR 23R, from BS 282 to BS 298. If
cracks are found, or if the skin is less than 0.056 inch thick, the
service bulletin describes procedures for 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. Therefore, we are proposing this AD, which
accomplishes the actions specified in the service information described
previously, except as discussed under ``Difference Between the Proposed
AD and the Service Bulletin.''
Difference Between the Proposed AD and the Service Bulletin
The ``Effectivity'' paragraph in Boeing Special Attention Service
Bulletin 747-53-2493, dated July 3, 2003, states that the service
bulletin applies to all Boeing Model 747-200C and all Boeing Model 747-
200F series airplanes. However, there was an unintended omission in the
service bulletin. This proposed AD would apply only to Boeing Model
747-200C and Boeing Model 747-200F series airplanes that are equipped
with a nose cargo door. This difference has been coordinated with the
manufacturer.
Clarification of Inspection Language
The service bulletin refers to a detailed visual inspection.
However, this proposed AD refers to this inspection as a ``detailed
inspection.'' Note 1 of this proposed AD defines a detailed inspection.
Costs of Compliance
There are about 77 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.
[[Page 14589]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hour Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections....................................... 6 $65 None $390 20 $7,800
--------------------------------------------------------------------------------------------------------------------------------------------------------
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. 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 FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA-2005-20690; Directorate Identifier 2003-NM-
230-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by May 9, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-200C and 747-200F series
airplanes, equipped with a nose cargo door, certificated in any
category; as identified in paragraph 1.A.1 of Boeing Special
Attention Service Bulletin 747-53-2493, dated July 3, 2003.
Unsafe Condition
(d) This AD was prompted by a report of a crack above the
stringer (STR) 23 lap splice on a 747-200F series airplane. We are
issuing this AD to detect and correct cracks or material loss in the
fuselage skin, and consequent reduced structural integrity of the
skin panel, which could result in rapid depressurization 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.
Inspections and Repair
(f) Before the accumulation of 15,000 total flight cycles, or
within 1,200 flight cycles after the effective date of this AD,
whichever occurs later: Do a detailed inspection for cracking, and a
low frequency eddy current inspection for material loss, in the
fuselage skin. Repair any crack or material loss prior to further
flight. Do all actions in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-53-
2493, dated July 3, 2003.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
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 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 March 14, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-5695 Filed 3-22-05; 8:45 am]
BILLING CODE 4910-13-P
