Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP Series Airplanes, 37130-37132 [E7-13263]
Download as PDF
<![CDATA[
37130
Federal Register / Vol. 72, No. 130 / Monday, July 9, 2007 / Proposed Rules
TABLE 3.—V2525–D5 AND V2528–D5 PARTS TO BE REMOVED—Continued
ATA chapter
reference
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
P/N
Nomenclature
................
................
................
................
................
................
2A2056 ..................
2A2931 ..................
2A3526 ..................
2A0847 ..................
2A1205–01 ............
2A3078–01 ............
Seal Assy, No. 4 Bearing, Rear.
Seal Assy, No. 4 Bearing, Rear.
Seal Assy, No. 4 Bearing, Rear.
Seal Ring Holder.
Duct Assy, Cooling Air, No. 4 Bearing, Rear.
Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72–45–11 ................
72–45–11 ................
2A3182 ..................
2A2354 ..................
Metering Plug, HPT Hub, Stage 1.
Metering Plug, HPT Hub, Stage 1.
72–45–13 ................
72–45–13 ................
2A1352 ..................
2A3032 ..................
Seal Air, HPT Stage 1.
Seal Air, HPT Stage 1.
All Engines
(j) After the effective date of this AD, do
not install any part that has a P/N listed in
this AD.
Alternative Methods of Compliance
(k) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(l) International Aero Engines nonmodification Service Bulletin No. V2500ENG–72–0541, Revision 1, dated February
26, 2007, pertains to the subject of this AD.
Issued in Burlington, Massachusetts, on
July 2, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–13256 Filed 7–6–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28620; Directorate
Identifier 2007–NM–090–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).
pwalker on PROD1PC71 with NOTICES2
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 747–100, 747–
100B, 747–100B SUD, 747–200B, 747–
200C, 747–200F, 747–300, 747SR, and
VerDate Aug<31>2005
16:43 Jul 06, 2007
Jkt 211001
747SP series airplanes. This proposed
AD would require repetitive inspections
for cracking of the station (STA) 1241
bulkhead fittings just above the canted
pressure deck; a one-time determination
of the edge margin at seven fastener
positions on each side of the airplane;
and related investigative/corrective
actions if necessary. This proposed AD
results from a report that an operator
found a 1.65-inch crack on the STA
1241 bulkhead fitting on the left side of
a Boeing Model 747–200F series
airplane that had accumulated 17,332
total flight cycles. We are proposing this
AD to detect and correct cracking in the
STA 1241 bulkhead fittings, which
could result in reduced structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by August 23, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
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–2007–28620; Directorate
Identifier 2007–NM–090–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 airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Operations office (telephone (800) 647–
E:\FR\FM\09JYP1.SGM
09JYP1
Federal Register / Vol. 72, No. 130 / Monday, July 9, 2007 / Proposed Rules
5527) is located on the ground floor of
the West Building at the street address
stated in the ADDRESSES section.
Discussion
We have received a report that an
operator found a 1.65-inch crack on the
station (STA) 1241 bulkhead fitting on
the left side of a Boeing Model 747–
200F series airplane that had
accumulated 17,332 total flight cycles.
The crack was at a fastener hole just
above the canted pressure deck. The
STA 1241 fitting was replaced on this
airplane. The STA 1241 bulkhead
fittings on Model 747 airplanes are 140inch long aluminum forgings that
extend from stringer 19 down through
the pressure deck and attach to the wing
rear spar. Cracking in the STA 1241
bulkhead fittings, if not found and
repaired, can become large and result in
reduced structural integrity of the
airplane.
pwalker on PROD1PC71 with NOTICES2
Other Relevant Rulemaking
On January 16, 1990, we issued AD
90–06–06, amendment 39–6490, (55 FR
8374, March 7, 1990), for certain Boeing
Model 747 series airplanes listed in
Boeing Document No. D6–35999, dated
March 31, 1989. That AD requires,
among other actions, replacement of the
STA 1241 bulkhead splice straps in
accordance with Boeing Service Bulletin
747–53–2283, Revision 3, dated
November 1, 1989. We issued that AD
to prevent structural failure of the
affected airplanes. The date of that
replacement is used to determine the
compliance threshold for certain
airplanes affected by this proposed AD.
On March 18, 1992, we issued AD 92–
08–02, amendment 39–8213 (57 FR
12869, April 14, 1992), for certain
Boeing Model 747 airplanes. That AD
requires repetitive inspections of the
STA 1241 bulkhead splice straps in
accordance with Boeing Service Bulletin
747–53–2283, Revision 3, dated
November 1, 1989, and repair if
necessary. Boeing Service Bulletin 747–
53–2219 is an alternative method of
compliance (AMOC) for certain repairs
required by that AD. The date of
modification in accordance with Boeing
Service Bulletin 747–53–2219 is used to
determine the compliance threshold for
certain airplanes affected by this
proposed AD.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 747–53A2658, dated
February 22, 2007. The service bulletin
describes procedures for doing
repetitive inspections (internal surface
high frequency eddy current and
external ultrasonic) for cracking of the
VerDate Aug<31>2005
16:43 Jul 06, 2007
Jkt 211001
STA 1241 bulkhead fittings just above
the canted pressure deck. The service
bulletin also specifies a one-time
determination of the edge margin at
seven fastener positions on each side of
the airplane. If the edge margin of a
fastener hole is less than 1.35 times the
diameter of the hole, the related
investigative/corrective action is
contacting Boeing for special inspection
data. For any crack found during a
repetitive inspection, the corrective
action is contacting Boeing for repair
data.
The compliance threshold for doing
the initial inspection varies according to
the configuration of the airplane, and
according to the date of previous splice
strap replacement or date of previous
bulkhead modification as described
above under ‘‘Other Relevant
Rulemaking.’’ The thresholds described
in Boeing Alert Service Bulletin 747–
53A2658 are as follows:
• For airplanes in the original
configuration, or as modified in
accordance with Boeing Service Bulletin
747–53–2219 (AMOC for AD 92–08–02):
Before the accumulation of 10,000 total
flight cycles, or 1,500 flight cycles after
the effective date on Boeing Alert
Service Bulletin 747–53A2658,
whichever occurs later.
• For airplanes modified in
accordance with Boeing Service Bulletin
747–53–2283 (AD 90–06–06): Before the
accumulation of 5,000 flight cycles
since modification in accordance with
Boeing Service Bulletin 747–53–2283,
or within 1,500 flight cycles after the
date on Boeing Alert Service Bulletin
747–53A2658, whichever occurs later.
The compliance time for doing the
first repeat inspection varies according
to the smallest calculated edge margin at
the seven fastener positions on each
side of the airplane. The earliest
specified range for doing the first
repetitive inspection is before the
accumulation of 11,500 total flight
cycles, or within 1,500 flight cycles
since the initial inspection, whichever
occurs later. The latest specified range
for doing the first repeat inspection is
before the accumulation of 15,000 total
flight cycles, or within 5,000 flight
cycles since the initial inspection,
whichever occurs later. Afterward, the
repetitive intervals range from intervals
not to exceed 1,500 flight cycles, to
intervals not to exceed 5,000 flight
cycles.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
37131
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 the Service Bulletin.’’
Difference Between the Proposed AD
and the Service Bulletin
The service bulletin specifies to
contact the manufacturer for
instructions on how to do certain
inspections and repairs, but this
proposed AD would require inspection
or repair 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 455 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about
133 airplanes of U.S. registry. The
proposed actions would take about 14
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
$148,960, or $1,120 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\09JYP1.SGM
09JYP1
37132
Federal Register / Vol. 72, No. 130 / Monday, July 9, 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–2007–28620;
Directorate Identifier 2007–NM–090–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by August 23, 2007.
pwalker on PROD1PC71 with NOTICES2
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–200C, 747–200F, 747–300, 747SR, and
747SP series airplanes, certificated in any
category; as identified in Boeing Alert
Service Bulletin 747–53A2658, dated
February 22, 2007.
VerDate Aug<31>2005
16:43 Jul 06, 2007
Jkt 211001
Unsafe Condition
(d) This AD results from a report that an
operator found a 1.65-inch crack on the
station (STA) 1241 bulkhead fitting on the
left side of a Boeing Model 747–200F series
airplane that had accumulated 17,332 total
flight cycles. We are issuing this AD to detect
and correct cracking in the STA 1241
bulkhead fittings, which could result in
reduced structural integrity 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 Corrective Action
(f) At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2658, dated
February 22, 2007: Do internal surface highfrequency eddy current and external
ultrasonic inspections for cracking of the
STA 1241 bulkhead fittings just above the
canted pressure deck; determine the edge
margin at seven fastener positions on each
side of the airplane; and do all applicable
related investigative/corrective actions; by
doing all of the actions specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2658, dated
February 22, 2007, except as provided by
paragraphs (f)(1) and (f)(2) of this AD. Do all
applicable related investigative/corrective
actions before further flight. Repeat the
inspections thereafter at the applicable
interval specified in paragraph 1.E.,
‘‘Compliance’’ of the service bulletin.
(1) Where the service bulletin specifies to
contact Boeing for appropriate action, before
further flight, do the action using a method
approved in accordance with the procedures
specified in paragraph (g) of this AD.
(2) Where the service bulletin specifies a
compliance time after the date on the service
bulletin, this AD requires compliance within
the specified compliance time after the
effective date 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) 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.
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
Issued in Renton, Washington, on June 25,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–13263 Filed 7–6–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28598; Directorate
Identifier 2007–NM–036–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757–200, –200CB, –200PF, and
–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Boeing Model 757–200, –200CB,
–200PF, and –300 series airplanes. This
proposed AD would require installation
of an automatic shutoff system for the
center tank fuel boost pumps, and
installation of a placard in the airplane
flight deck if necessary. This proposed
AD would also require revisions to the
Limitations and Normal Procedures
sections of the airplane flight manual to
advise the flightcrew of certain
operating restrictions for airplanes
equipped with an automated center tank
fuel pump shutoff control. This
proposed AD would also require a
revision to the Airworthiness
Limitations (AWLs) section of the
Instructions for Continued
Airworthiness to incorporate AWL No.
28–AWL–20 and No. 28–AWL–26. This
proposed AD would also require
replacement of the fuel control panel
assembly with a modified part,
installation of two secondary pump
control relays for the center tank fuel
pumps, other specified actions, and
concurrent modification of the fuel
control panel assembly. This proposed
AD results from fuel system reviews
conducted by the manufacturer. We are
proposing this AD to prevent center
tank fuel pump operation with
continuous low pressure, which could
lead to friction sparks or overheating in
the fuel pump inlet or could create a
potential ignition source inside the
center fuel tank; these conditions, in
combination with flammable fuel
vapors, could result in a center fuel tank
E:\FR\FM\09JYP1.SGM
09JYP1
]]>Agencies
[Federal Register Volume 72, Number 130 (Monday, July 9, 2007)]
[Proposed Rules]
[Pages 37130-37132]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13263]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28620; Directorate Identifier 2007-NM-090-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
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, 747-100B, 747-100B SUD, 747-200B,
747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This
proposed AD would require repetitive inspections for cracking of the
station (STA) 1241 bulkhead fittings just above the canted pressure
deck; a one-time determination of the edge margin at seven fastener
positions on each side of the airplane; and related investigative/
corrective actions if necessary. This proposed AD results from a report
that an operator found a 1.65-inch crack on the STA 1241 bulkhead
fitting on the left side of a Boeing Model 747-200F series airplane
that had accumulated 17,332 total flight cycles. We are proposing this
AD to detect and correct cracking in the STA 1241 bulkhead fittings,
which could result in reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by August 23, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for the service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: 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-
28620; Directorate Identifier 2007-NM-090-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 airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Operations
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Operations office (telephone (800) 647-
[[Page 37131]]
5527) is located on the ground floor of the West Building at the street
address stated in the ADDRESSES section.
Discussion
We have received a report that an operator found a 1.65-inch crack
on the station (STA) 1241 bulkhead fitting on the left side of a Boeing
Model 747-200F series airplane that had accumulated 17,332 total flight
cycles. The crack was at a fastener hole just above the canted pressure
deck. The STA 1241 fitting was replaced on this airplane. The STA 1241
bulkhead fittings on Model 747 airplanes are 140-inch long aluminum
forgings that extend from stringer 19 down through the pressure deck
and attach to the wing rear spar. Cracking in the STA 1241 bulkhead
fittings, if not found and repaired, can become large and result in
reduced structural integrity of the airplane.
Other Relevant Rulemaking
On January 16, 1990, we issued AD 90-06-06, amendment 39-6490, (55
FR 8374, March 7, 1990), for certain Boeing Model 747 series airplanes
listed in Boeing Document No. D6-35999, dated March 31, 1989. That AD
requires, among other actions, replacement of the STA 1241 bulkhead
splice straps in accordance with Boeing Service Bulletin 747-53-2283,
Revision 3, dated November 1, 1989. We issued that AD to prevent
structural failure of the affected airplanes. The date of that
replacement is used to determine the compliance threshold for certain
airplanes affected by this proposed AD.
On March 18, 1992, we issued AD 92-08-02, amendment 39-8213 (57 FR
12869, April 14, 1992), for certain Boeing Model 747 airplanes. That AD
requires repetitive inspections of the STA 1241 bulkhead splice straps
in accordance with Boeing Service Bulletin 747-53-2283, Revision 3,
dated November 1, 1989, and repair if necessary. Boeing Service
Bulletin 747-53-2219 is an alternative method of compliance (AMOC) for
certain repairs required by that AD. The date of modification in
accordance with Boeing Service Bulletin 747-53-2219 is used to
determine the compliance threshold for certain airplanes affected by
this proposed AD.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-53A2658, dated
February 22, 2007. The service bulletin describes procedures for doing
repetitive inspections (internal surface high frequency eddy current
and external ultrasonic) for cracking of the STA 1241 bulkhead fittings
just above the canted pressure deck. The service bulletin also
specifies a one-time determination of the edge margin at seven fastener
positions on each side of the airplane. If the edge margin of a
fastener hole is less than 1.35 times the diameter of the hole, the
related investigative/corrective action is contacting Boeing for
special inspection data. For any crack found during a repetitive
inspection, the corrective action is contacting Boeing for repair data.
The compliance threshold for doing the initial inspection varies
according to the configuration of the airplane, and according to the
date of previous splice strap replacement or date of previous bulkhead
modification as described above under ``Other Relevant Rulemaking.''
The thresholds described in Boeing Alert Service Bulletin 747-53A2658
are as follows:
For airplanes in the original configuration, or as
modified in accordance with Boeing Service Bulletin 747-53-2219 (AMOC
for AD 92-08-02): Before the accumulation of 10,000 total flight
cycles, or 1,500 flight cycles after the effective date on Boeing Alert
Service Bulletin 747-53A2658, whichever occurs later.
For airplanes modified in accordance with Boeing Service
Bulletin 747-53-2283 (AD 90-06-06): Before the accumulation of 5,000
flight cycles since modification in accordance with Boeing Service
Bulletin 747-53-2283, or within 1,500 flight cycles after the date on
Boeing Alert Service Bulletin 747-53A2658, whichever occurs later.
The compliance time for doing the first repeat inspection varies
according to the smallest calculated edge margin at the seven fastener
positions on each side of the airplane. The earliest specified range
for doing the first repetitive inspection is before the accumulation of
11,500 total flight cycles, or within 1,500 flight cycles since the
initial inspection, whichever occurs later. The latest specified range
for doing the first repeat inspection is before the accumulation of
15,000 total flight cycles, or within 5,000 flight cycles since the
initial inspection, whichever occurs later. Afterward, the repetitive
intervals range from intervals not to exceed 1,500 flight cycles, to
intervals not to exceed 5,000 flight cycles.
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 the Service Bulletin.''
Difference Between the Proposed AD and the Service Bulletin
The service bulletin specifies to contact the manufacturer for
instructions on how to do certain inspections and repairs, but this
proposed AD would require inspection or repair 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 455 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 133 airplanes of
U.S. registry. The proposed actions would take about 14 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
$148,960, or $1,120 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 37132]]
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-2007-28620; Directorate Identifier 2007-
NM-090-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by August
23, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series
airplanes, certificated in any category; as identified in Boeing
Alert Service Bulletin 747-53A2658, dated February 22, 2007.
Unsafe Condition
(d) This AD results from a report that an operator found a 1.65-
inch crack on the station (STA) 1241 bulkhead fitting on the left
side of a Boeing Model 747-200F series airplane that had accumulated
17,332 total flight cycles. We are issuing this AD to detect and
correct cracking in the STA 1241 bulkhead fittings, which could
result in reduced structural integrity 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 Corrective Action
(f) At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2658, dated
February 22, 2007: Do internal surface high-frequency eddy current
and external ultrasonic inspections for cracking of the STA 1241
bulkhead fittings just above the canted pressure deck; determine the
edge margin at seven fastener positions on each side of the
airplane; and do all applicable related investigative/corrective
actions; by doing all of the actions specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2658, dated
February 22, 2007, except as provided by paragraphs (f)(1) and
(f)(2) of this AD. Do all applicable related investigative/
corrective actions before further flight. Repeat the inspections
thereafter at the applicable interval specified in paragraph 1.E.,
``Compliance'' of the service bulletin.
(1) Where the service bulletin specifies to contact Boeing for
appropriate action, before further flight, do the action using a
method approved in accordance with the procedures specified in
paragraph (g) of this AD.
(2) Where the service bulletin specifies a compliance time after
the date on the service bulletin, this AD requires compliance within
the specified compliance time after the effective date 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) 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 June 25, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-13263 Filed 7-6-07; 8:45 am]
BILLING CODE 4910-13-P
