Airworthiness Directives; Boeing Model 747 Airplanes, 45973-45976 [E7-16121]
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Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules
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.
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 1,949 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about
660 airplanes of U.S. registry. The
modification and installation actions
would take about 2 work hours per
airplane, at an average labor rate of $80
per work hour. Required parts would
cost about $207 per airplane. Based on
these figures, the estimated cost of the
proposed AD for U.S. operators is
$242,220, or $367 per airplane.
List of Subjects in 14 CFR Part 39
rwilkins on PROD1PC63 with PROPOSALS
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
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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–2007–28921;
Directorate Identifier 2007–NM–091–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by October 1, 2007.
Affected ADs
(b) None.
Unsafe Condition
(d) This AD results from reports indicating
that the forward door escape slide inflated 90
degrees out of alignment after deployment
from the forward right side slide
compartment. We are issuing this AD to
prevent the escape slide from being unusable
during an emergency evacuation and
consequent injury to passengers or
crewmembers.
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.
Modification and Installation
(f) Within 60 months after the effective
date of this AD, modify the door-mounted
escape system of the forward right side door
slide compartment, in accordance with the
Frm 00026
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–25–
1567, dated March 21, 2007.
Prior to or Concurrent Requirement
(g) Prior to or concurrently with the
requirements of paragraph (f) of this AD,
accomplish the requirements of AD 2004–02–
08, amendment 39–13443.
Alternative Methods of Compliance
(AMOCs)
(h)(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.
Issued in Renton, Washington, on July 30,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–16110 Filed 8–15–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28989; Directorate
Identifier 2007–NM–070–AD]
RIN 2120–AA64
Applicability
(c) This AD applies to Boeing Model 737–
300, –400, and –500 series airplanes,
certificated in any category; as identified in
Boeing Special Attention Service Bulletin
737–25–1567, dated March 21, 2007.
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45973
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Sfmt 4702
Airworthiness Directives; Boeing
Model 747 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Boeing Model 747–200B, 747–200C,
747–200F, 747–300, 747–400, and
747SP series airplanes. The existing AD
currently requires doing a detailed
inspection of the left and right longeron
extension fittings, and corrective action
if necessary. This proposed AD would
add airplanes to the applicability of the
existing AD. This proposed AD results
from reports that accidental drilling
damage to the longeron extension
fittings was found on airplanes not
subject to the existing AD. We are
proposing this AD to detect and correct
accidental drilling damage of the
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Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules
longeron extension fittings, which could
lead to cracking of the longeron
extension fittings and result in rapid
decompression of the airplane.
DATES: We must receive comments on
this proposed AD by October 1, 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 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:
rwilkins on PROD1PC63 with PROPOSALS
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 ‘‘Docket No. FAA–2007–28989;
Directorate Identifier 2007–NM–070–
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
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Jkt 211001
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 the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or may can visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
ground floor of the West Building at the
DOT street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
the Docket Management System receives
them.
the same as the original issue, except
that airplanes have been added to its
effectivity.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to develop on
other airplanes of the same type design.
For this reason, we are proposing this
AD, which would supersede AD 2006–
10–04 and would retain certain
requirements of the existing AD. The
proposed AD would also add airplanes
to the applicability of the existing AD.
The proposed AD would remove the
reporting requirement of the existing
AD. The proposed AD would also
require accomplishing the actions
specified in the service information
described previously, except as
discussed under ‘‘Difference Between
the Proposed AD and the Service
Bulletin.’’
Discussion
On April 28, 2006, we issued AD
2006–10–04, amendment 39–14588 (71
FR 27592, May 12, 2006), for certain
Boeing Model 747–200B, 747–200C,
747–200F, 747–300, 747–400, and
747SP series airplanes. That AD
requires doing a detailed inspection of
the left and right longeron extension
fittings, and corrective action if
necessary. That AD resulted from
cracking found in the longeron
extension fitting at body station 1480
due to accidental damage during
production. We issued that AD to detect
and correct cracking in the longeron
extension fitting, which could result in
rapid decompression of the airplane.
Difference Between the Proposed AD
and the Service Bulletin
Actions Since Existing AD Was Issued
Since we issued AD 2006–10–04, we
received reports that accidental drill
damage was discovered during
inspections of the longeron extension
fittings of five airplanes not subject to
that AD, including one airplane
manufactured before the airplanes
specified in the effectivity of Boeing
Alert Service Bulletin 747–53A2515,
dated October 20, 2005 (cited in AD
2006–10–04 as the appropriate source of
service information). Boeing therefore
concluded that additional airplanes
which might be subject to the unsafe
condition should be added to the
effectivity of a revision of that service
bulletin.
Interim Action
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 747–53A2515, Revision
1, dated March 1, 2007. Revision 1 of
the alert service bulletin is essentially
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Fmt 4702
Sfmt 4702
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.
We consider this proposed AD
interim action. If final action is later
identified, we may consider further
rulemaking then.
Costs of Compliance
There are about 876 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about
156 airplanes of U.S. registry.
The actions specified by this
proposed AD were previously required
by AD 2006–10–04, which was
applicable to approximately 25
airplanes of U.S. registry. The actions
required by that AD take about 1 work
hour per airplane. We estimated the cost
of the current requirements of that AD
on U.S. operators to be $2,000, or $80
per airplane. Some operators of the 25
airplanes subject to AD 2006–10–04
may have already initiated the required
actions. This proposed AD would add
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Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules
no new costs associated with those
airplanes.
This proposed AD would be
applicable to approximately 131
additional airplanes of U.S. registry.
New actions required by this proposed
AD would take about 1 work hour per
airplane. Based on the current labor rate
of $80 per work hour, we estimate the
new costs imposed by this proposed AD
on U.S. operators to be $10,480, or $80
per airplane. This figure is based on
assumptions that no operator of these
additional airplanes has yet done any of
the proposed requirements of this AD,
and that no operator would do those
actions in the future if this AD were not
adopted.
rwilkins on PROD1PC63 with PROPOSALS
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
VerDate Aug<31>2005
17:19 Aug 15, 2007
Jkt 211001
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 removing amendment 39–14588 (71
FR 27592, May 12, 2006) and adding the
following new airworthiness directive
(AD):
BOEING: Docket No. FAA–2007–28989;
Directorate Identifier 2007–NM–070–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by October 1, 2007.
Affected ADs
(b) This AD supersedes AD 2006–10–04.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–200C, 747–200F, 747–300, 747–400,
747–400D, 747–400F, 747SR, and 747SP
series airplanes, certificated in any category;
as identified in Boeing Alert Service Bulletin
747–53A2515, Revision 1, dated March 1,
2007.
Unsafe Condition
(d) This AD results from reports that
accidental drilling damage to the longeron
extension fittings was found on airplanes not
subject to the existing AD. We are issuing
this AD to detect and correct accidental
drilling damage of the longeron extension
fittings, which could lead to cracking of the
longeron extension fittings and result in
rapid decompression of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD
2006–10–04
Detailed Inspection
(f) For Group 1 airplanes identified in
Boeing Alert Service Bulletin 747–53A2515,
Revision 1, dated March 1, 2007: At the
applicable compliance time specified in
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45975
paragraph (f)(1) or (f)(2) of this AD, do a
detailed inspection of the left and right
longeron extension fittings for damage, and,
before further flight, do the corrective action
if applicable, by accomplishing all the
applicable actions specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2515, dated October
20, 2005; or Revision 1, dated March 1, 2007.
Note 1: Boeing Alert Service Bulletin 747–
53A2515, dated October 20, 2005; and
Revision 1, dated March 1, 2007; refer to
Boeing Alert Service Bulletin 747–53A2390,
Revision 1, dated July 6, 2000, as an
additional source of service information for
replacing a damaged longeron fitting with a
new longeron extension fitting.
(1) For airplanes that have accomplished
the inspection of the splice area for cracking
as specified in Boeing Alert Service Bulletin
747–53A2390, dated July 31, 1997; or
Revision 1, dated July 6, 2000: Inspect in
accordance with paragraph (f) of this AD
before the airplane has accumulated 10,000
total flight cycles, or within 1,000 flight
cycles after June 16, 2006 (the effective date
of AD 2006–10–04), whichever is later.
(2) For airplanes that have not
accomplished the inspection of the splice
area for cracking as specified in Boeing Alert
Service Bulletin 747–53A2390, dated July 31,
1997; or Revision 1, dated July 6, 2000:
Inspect in accordance with paragraph (f) of
this AD before the airplane has accumulated
10,000 total flight cycles, or within 250 flight
cycles after June 16, 2006, whichever is later.
New Requirements of This AD
Detailed Inspection of Additional Airplanes
(g) For Group 2 and Group 3 airplanes
identified in Boeing Alert Service Bulletin
747–53A2515, Revision 1, dated March 1,
2007: Except as provided by paragraphs (h)
and (i) of this AD, at the applicable time
specified in paragraph 1.E of Boeing Alert
Service Bulletin 747–53A2515, Revision 1,
dated March 1, 2007, do a detailed inspection
of the left and right longeron extension
fittings for damage and, before further flight,
do the corrective action, as applicable; by
accomplishing all the applicable actions
specified in the Accomplishment
Instructions of the alert service bulletin.
Compliance Times
(h) Where the alert service bulletin
specifies compliance times relative to the
release date of the alert service bulletin, this
AD requires compliance at compliance times
relative to the effective date of this AD.
Repair of Certain Conditions
(i) If any damage is found during any
inspection required by this AD and the
service bulletin specifies to contact Boeing
for appropriate action: Before further flight,
repair the damage using a method approved
in accordance with the procedures specified
in paragraph (k) of this AD.
Credit for Actions Done Using Previous
Service Information
(j) Actions done before the effective date of
this AD in accordance with Boeing Alert
Service Bulletin 747–53A2515, dated October
20, 2005, are considered acceptable for
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Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules
compliance with the corresponding actions
of this AD.
Alternative Methods of Compliance
(AMOCs)
(k)(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) AMOCs approved previously in
accordance with AD 2006–10–04, are
approved as AMOCs for the corresponding
provisions of this AD.
(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.
(4) 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.
engines were running, the aircraft started
moving again despite parking brake
application. Captain tried to stop the aircraft
via the pedals but, as the parking brake
selector valve was selected, the aircraft could
not be stopped (as per design, activation of
the parking brake inhibits the other braking
modes, and consequently prevents the
recovery of the normal braking through the
pedals). As part of the investigation, the
pressure limiter was removed and examined.
The expertise revealed a metallic wire aimed
at reducing the section of one port of this
equipment was found broken. A part of this
wire partially obstructed the hole receiving
this wire, thus delaying the build up of
parking brake pressure.
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
We must receive comments on
this proposed AD by September 17,
2007.
DATES:
14 CFR Part 39
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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• 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.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
[Docket No. FAA–2007–28922; Directorate
Identifier 2007–NM–132–AD]
Examining the AD Docket
Issued in Renton, Washington, on July 30,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–16121 Filed 8–15–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
rwilkins on PROD1PC63 with PROPOSALS
AGENCY:
SUMMARY: 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:
An incident occurred on one A300–600
aircraft at parking brake application. Both
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ADDRESSES:
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this proposed
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–28922; Directorate Identifier
2007–NM–132–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on 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 we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2007–0151,
dated May 22, 2007 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
An incident occurred on one A300–600
aircraft at parking brake application. Both
engines were running, the aircraft started
moving again despite parking brake
application. Captain tried to stop the aircraft
via the pedals but, as the parking brake
selector valve was selected, the aircraft could
not be stopped (as per design, activation of
the parking brake inhibits the other braking
modes, and consequently prevents the
recovery of the normal braking through the
pedals). As part of the investigation, the
pressure limiter was removed and examined.
The expertise revealed a metallic wire aimed
at reducing the section of one port of this
equipment was found broken. A part of this
wire partially obstructed the hole receiving
this wire, thus delaying the build up of
parking brake pressure. In order to avoid
recurrence of the failure mode described
above, EASA issued Airworthiness Directive
(AD) 2006–0178 to require the replacement of
the parking brake pressure limiter (FIN
323292).
During embodiment of SB (Service
Bulletin) 32–2133 on an A310 as per AD
2006–0178 (EASA AD 2006–0178
corresponds to FAA AD 2007–02–21,
amendment 39–14908), an operator reported
that the modified pressure limiter could not
be fitted. Subsequent investigation concluded
that A310 installation being slightly different
from A300–600 aircraft, the approved
solution was not directly adaptable to A310
aircraft.
* * * This new AD, dealing with the same
subject, requires the replacement of the brake
pressure limiter by accomplishment of
Airbus SB A310–32–2133, which has been
E:\FR\FM\16AUP1.SGM
16AUP1
]]>Agencies
[Federal Register Volume 72, Number 158 (Thursday, August 16, 2007)]
[Proposed Rules]
[Pages 45973-45976]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-16121]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28989; Directorate Identifier 2007-NM-070-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Boeing Model 747-200B, 747-200C,
747-200F, 747-300, 747-400, and 747SP series airplanes. The existing AD
currently requires doing a detailed inspection of the left and right
longeron extension fittings, and corrective action if necessary. This
proposed AD would add airplanes to the applicability of the existing
AD. This proposed AD results from reports that accidental drilling
damage to the longeron extension fittings was found on airplanes not
subject to the existing AD. We are proposing this AD to detect and
correct accidental drilling damage of the
[[Page 45974]]
longeron extension fittings, which could lead to cracking of the
longeron extension fittings and result in rapid decompression of the
airplane.
DATES: We must receive comments on this proposed AD by October 1, 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 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 ``Docket No.
FAA-2007-28989; Directorate Identifier 2007-NM-070-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 the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or may
can visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The
Docket Operations office (telephone (800) 647-5527) is located on the
ground floor of the West Building at the DOT street address stated in
the ADDRESSES section. Comments will be available in the AD docket
shortly after the Docket Management System receives them.
Discussion
On April 28, 2006, we issued AD 2006-10-04, amendment 39-14588 (71
FR 27592, May 12, 2006), for certain Boeing Model 747-200B, 747-200C,
747-200F, 747-300, 747-400, and 747SP series airplanes. That AD
requires doing a detailed inspection of the left and right longeron
extension fittings, and corrective action if necessary. That AD
resulted from cracking found in the longeron extension fitting at body
station 1480 due to accidental damage during production. We issued that
AD to detect and correct cracking in the longeron extension fitting,
which could result in rapid decompression of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2006-10-04, we received reports that accidental
drill damage was discovered during inspections of the longeron
extension fittings of five airplanes not subject to that AD, including
one airplane manufactured before the airplanes specified in the
effectivity of Boeing Alert Service Bulletin 747-53A2515, dated October
20, 2005 (cited in AD 2006-10-04 as the appropriate source of service
information). Boeing therefore concluded that additional airplanes
which might be subject to the unsafe condition should be added to the
effectivity of a revision of that service bulletin.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-53A2515,
Revision 1, dated March 1, 2007. Revision 1 of the alert service
bulletin is essentially the same as the original issue, except that
airplanes have been added to its effectivity.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2006-10-04 and would retain certain requirements of
the existing AD. The proposed AD would also add airplanes to the
applicability of the existing AD. The proposed AD would remove the
reporting requirement of the existing AD. The proposed AD would also
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 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.
Interim Action
We consider this proposed AD interim action. If final action is
later identified, we may consider further rulemaking then.
Costs of Compliance
There are about 876 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 156 airplanes of
U.S. registry.
The actions specified by this proposed AD were previously required
by AD 2006-10-04, which was applicable to approximately 25 airplanes of
U.S. registry. The actions required by that AD take about 1 work hour
per airplane. We estimated the cost of the current requirements of that
AD on U.S. operators to be $2,000, or $80 per airplane. Some operators
of the 25 airplanes subject to AD 2006-10-04 may have already initiated
the required actions. This proposed AD would add
[[Page 45975]]
no new costs associated with those airplanes.
This proposed AD would be applicable to approximately 131
additional airplanes of U.S. registry. New actions required by this
proposed AD would take about 1 work hour per airplane. Based on the
current labor rate of $80 per work hour, we estimate the new costs
imposed by this proposed AD on U.S. operators to be $10,480, or $80 per
airplane. This figure is based on assumptions that no operator of these
additional airplanes has yet done any of the proposed requirements of
this AD, and that no operator would do those actions in the future if
this AD were not adopted.
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.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14588 (71 FR 27592, May 12, 2006) and adding the
following new airworthiness directive (AD):
BOEING: Docket No. FAA-2007-28989; Directorate Identifier 2007-NM-
070-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
1, 2007.
Affected ADs
(b) This AD supersedes AD 2006-10-04.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-
400F, 747SR, and 747SP series airplanes, certificated in any
category; as identified in Boeing Alert Service Bulletin 747-
53A2515, Revision 1, dated March 1, 2007.
Unsafe Condition
(d) This AD results from reports that accidental drilling damage
to the longeron extension fittings was found on airplanes not
subject to the existing AD. We are issuing this AD to detect and
correct accidental drilling damage of the longeron extension
fittings, which could lead to cracking of the longeron extension
fittings and result in rapid decompression of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD 2006-10-04
Detailed Inspection
(f) For Group 1 airplanes identified in Boeing Alert Service
Bulletin 747-53A2515, Revision 1, dated March 1, 2007: At the
applicable compliance time specified in paragraph (f)(1) or (f)(2)
of this AD, do a detailed inspection of the left and right longeron
extension fittings for damage, and, before further flight, do the
corrective action if applicable, by accomplishing all the applicable
actions specified in the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2515, dated October 20, 2005; or Revision 1,
dated March 1, 2007.
Note 1: Boeing Alert Service Bulletin 747-53A2515, dated October
20, 2005; and Revision 1, dated March 1, 2007; refer to Boeing Alert
Service Bulletin 747-53A2390, Revision 1, dated July 6, 2000, as an
additional source of service information for replacing a damaged
longeron fitting with a new longeron extension fitting.
(1) For airplanes that have accomplished the inspection of the
splice area for cracking as specified in Boeing Alert Service
Bulletin 747-53A2390, dated July 31, 1997; or Revision 1, dated July
6, 2000: Inspect in accordance with paragraph (f) of this AD before
the airplane has accumulated 10,000 total flight cycles, or within
1,000 flight cycles after June 16, 2006 (the effective date of AD
2006-10-04), whichever is later.
(2) For airplanes that have not accomplished the inspection of
the splice area for cracking as specified in Boeing Alert Service
Bulletin 747-53A2390, dated July 31, 1997; or Revision 1, dated July
6, 2000: Inspect in accordance with paragraph (f) of this AD before
the airplane has accumulated 10,000 total flight cycles, or within
250 flight cycles after June 16, 2006, whichever is later.
New Requirements of This AD
Detailed Inspection of Additional Airplanes
(g) For Group 2 and Group 3 airplanes identified in Boeing Alert
Service Bulletin 747-53A2515, Revision 1, dated March 1, 2007:
Except as provided by paragraphs (h) and (i) of this AD, at the
applicable time specified in paragraph 1.E of Boeing Alert Service
Bulletin 747-53A2515, Revision 1, dated March 1, 2007, do a detailed
inspection of the left and right longeron extension fittings for
damage and, before further flight, do the corrective action, as
applicable; by accomplishing all the applicable actions specified in
the Accomplishment Instructions of the alert service bulletin.
Compliance Times
(h) Where the alert service bulletin specifies compliance times
relative to the release date of the alert service bulletin, this AD
requires compliance at compliance times relative to the effective
date of this AD.
Repair of Certain Conditions
(i) If any damage is found during any inspection required by
this AD and the service bulletin specifies to contact Boeing for
appropriate action: Before further flight, repair the damage using a
method approved in accordance with the procedures specified in
paragraph (k) of this AD.
Credit for Actions Done Using Previous Service Information
(j) Actions done before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 747-53A2515, dated
October 20, 2005, are considered acceptable for
[[Page 45976]]
compliance with the corresponding actions of this AD.
Alternative Methods of Compliance (AMOCs)
(k)(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) AMOCs approved previously in accordance with AD 2006-10-04,
are approved as AMOCs for the corresponding provisions of this AD.
(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.
(4) 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 July 30, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-16121 Filed 8-15-07; 8:45 am]
BILLING CODE 4910-13-P
