Airworthiness Directives; Airbus Model A300 B4-600R and A300 F4-600R Series Airplanes, 5620-5623 [E6-1418]
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5620
Proposed Rules
Federal Register
Vol. 71, No. 22
Thursday, February 2, 2006
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6450; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20691; Directorate
Identifier 2004–NM–249–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757–200 and –300 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Proposed rule; withdrawal.
hsrobinson on PROD1PC71 with PROPOSALS
AGENCY:
SUMMARY: The FAA withdraws a notice
of proposed rulemaking (NPRM) that
proposed a new airworthiness directive
(AD) for certain Boeing Model 757–200
and –300 series airplanes. The proposed
AD would have required inspecting for
the part number, the serial number, and
the mark ‘‘RETESTED’’ on the reaction
link of the main landing gear (MLG),
and replacing the reaction link of the
MLG with a retested reaction link if
necessary. Since the proposed AD was
issued, we have received new data that
all suspect reaction links of the MLG
have been replaced with acceptable
reaction links, and the suspect reaction
links have been sent back to the reaction
link manufacturer. Accordingly, the
proposed AD is withdrawn.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
Washington, DC. This docket number is
FAA–2005–20691; the directorate
identifier for this docket is 2004–NM–
249–AD.
FOR FURTHER INFORMATION CONTACT:
Dennis Stremick, Aerospace Engineer,
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15:25 Feb 01, 2006
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We proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR
part 39) with a notice of proposed
rulemaking (NPRM) for a new AD for
certain Boeing Model 757–200 and –300
series airplanes. That NPRM was
published in the Federal Register on
March 23, 2005 (70 FR 14585). The
NPRM would have required inspecting
for the part number, the serial number,
and the mark ‘‘RETESTED’’ on the
reaction link of the main landing gear
(MLG), and replacing the reaction link
of the MLG with a retested reaction link
if necessary. The NPRM resulted from a
report of faulty welds in certain reaction
links. The proposed actions were
intended 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.
Actions Since NPRM Was Issued
Since we issued the NPRM, we have
received confirmation that, world-wide,
all suspect reaction links of the MLG
have been replaced with acceptable
reaction links, and the suspect reaction
links have been sent back to the reaction
link manufacturer.
FAA’s Conclusions
Upon further consideration, we have
determined that the suspect reaction
links are not installed on any airplane
and have been altered in such a way as
to be impossible to be reinstalled on an
airplane. Accordingly, the NPRM is
withdrawn.
Withdrawal of the NPRM does not
preclude the FAA from issuing another
related action or commit the FAA to any
course of action in the future.
Regulatory Impact
Since this action only withdraws an
NPRM, it is neither a proposed nor a
final rule and therefore is not covered
under Executive Order 12866, the
Regulatory Flexibility Act, or DOT
Regulatory Policies and Procedures (44
FR 11034, February 26, 1979).
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Withdrawal
Accordingly, we withdraw the NPRM,
Docket No. FAA–2005–20691,
Directorate Identifier 2004–NM–249–
AD, which was published in the Federal
Register on March 23, 2005 (70 FR
14585).
Issued in Renton, Washington, on January
24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–1415 Filed 2–1–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23760; Directorate
Identifier 2005–NM–211–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B4–600R and A300 F4–600R
Series 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
Airbus Model A300 B4–600R and A300
F4–600R series airplanes. The existing
AD requires repetitive inspections for
damage of the center tank fuel pumps
and fuel pump canisters and
replacement of any damaged parts, and
mandates modification of the canisters
of the center tank fuel pumps, which
terminates the repetitive inspections.
For certain airplanes, this proposed AD
would require a one-time inspection of
the attachment bolts of the outlet flange
of the canisters of the center tank fuel
pumps for bolts that are too short and
do not protrude through the nut, and
replacement of the bolts if necessary.
This proposed AD results from several
reports that the attachment bolts for the
canisters, modified by the requirements
in the existing AD, are too short and do
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Federal Register / Vol. 71, No. 22 / Thursday, February 2, 2006 / Proposed Rules
not fully protrude from the nuts. We are
proposing this AD to prevent damage to
the fuel pump and fuel pump canister,
which could result in loss of flame trap
capability and could provide a fuel
ignition source in the center fuel tank.
DATES: We must receive comments on
this proposed AD by March 6, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT:
Thomas Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
hsrobinson on PROD1PC71 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–2006–23760;
Directorate Identifier 2005–NM–211–
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,
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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 you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
On November 1, 2004, we issued AD
2004–23–08, amendment 39–13863 (69
FR 65528, November 15, 2004), for
certain Airbus Model A300 B4–600R
and A300 F4–600R series airplanes.
That AD superseded AD 99–27–07,
amendment 39–11488 (65 FR 213,
January 4, 2000), to mandate
modification of the canisters of the
center tank fuel pumps, which would
terminate the repetitive inspections
required by AD 99–27–07. AD 2004–23–
08 resulted from the issuance of a new
French airworthiness directive, 2002–
132(B), dated March 20, 2002, which
mandated the modification. We issued
that AD to prevent damage to the fuel
pump and fuel pump canister, which
could result in loss of flame trap
capability and could provide a fuel
ignition source in the center fuel tank.
Actions Since Existing AD Was Issued
Since we issued AD 2004–23–08, the
Direction Gonorale de l’Aviation Civile
(DGAC), which is the airworthiness
authority for France, advises that it has
received several reports that the
attachment bolts for the canisters,
modified by the requirements in the
existing French AD, are too short and do
not fully protrude from the nuts. In light
of these findings, the DGAC has issued
French airworthiness directive F–2005–
147, dated August 17, 2005. French
airworthiness directive F–2005–147
adds a one-time inspection for bolts that
are too short and do not protrude from
the nut, and replacement of the bolts if
necessary.
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Relevant Service Information
Airbus has issued Service Bulletin
A300–28–6069, Revision 02, dated
October 17, 2003. For airplanes on
which the modification specified in the
original issue or Revision 01 of the
service bulletin has been accomplished,
Revision 02 includes additional work.
That additional work involves a onetime inspection of the attachment bolts
of the outlet flange of the canisters of
the center tank fuel pumps for bolts that
are too short and do not protrude from
the nut, and replacement of the bolts if
necessary.
Airbus has also issued Service
Bulletin A300–28–6087, dated April 8,
2005, for airplanes on which Airbus
Service Bulletin A300–28–6069, dated
September 4, 2001, or Revision 01,
dated May 28, 2002, has been
accomplished. The service bulletin
describes procedures for a one-time
inspection of the attachment bolts of the
outlet flange of the canisters of the
center tank fuel pumps for bolts that are
too short and do not protrude from the
nut, and replacement of the bolts if
necessary.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. The DGAC mandated the
service information and issued French
airworthiness directive F–2005–147,
dated August 17, 2005, to ensure the
continued airworthiness of these
airplanes in France.
FAA’s Determination and Requirements
of the Proposed AD
These airplane models are
manufactured in France and are type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, the DGAC has
kept the FAA informed of the situation
described above. We have examined the
DGAC’s findings, evaluated all pertinent
information, and determined that AD
action is necessary for airplanes of this
type design that are certificated for
operation in the United States.
This proposed AD would supersede
AD 2004–23–08 and would continue to
require repetitive inspections for
damage of the center tank fuel pumps
and fuel pump canisters and
replacement of any damaged parts, and
modification of the canisters of the
center tank fuel pumps, which
terminates the repetitive inspections.
For certain airplanes, this proposed AD
would also require a one-time
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inspection of the attachment bolts of the
outlet flange of the canisters of the
center tank fuel pumps for bolts that are
too short and do not protrude through
the nut, and replacement of the bolts if
necessary.
Difference Between Proposed AD and
French Airworthiness Directive
The applicability of the French
airworthiness directive excludes
airplanes on which Airbus Service
Bulletin A300–28–6069, Revision 2, or
A300–28–6087 were accomplished in
service. However, we have not excluded
those airplanes in the applicability of
this proposed AD; rather, this proposed
AD would include a requirement to
accomplish the actions specified in
those service bulletins. This proposed
requirement would ensure that the
actions specified in those service
bulletins are accomplished on all
affected airplanes. Operators must
continue to operate the airplane in the
configuration required by this proposed
AD unless an alternative method of
compliance is approved.
Clarification of Inspection Terminology
In this proposed AD, the ‘‘inspection’’
specified in the service bulletins is
referred to as a ‘‘detailed inspection.’’
Change to Existing AD
This proposed AD would retain the
requirements of the existing AD. Since
AD 2004–23–08 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2004–23–08
hsrobinson on PROD1PC71 with PROPOSALS
Paragraph
Paragraph
Paragraph
Paragraph
(a)
(b)
(c)
(d)
............
............
............
............
Corresponding
requirement in this
proposed AD
Paragraph
Paragraph
Paragraph
Paragraph
(f).
(g).
(h).
(i).
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Costs of Compliance
This proposed AD would affect about
101 airplanes of U.S. registry.
The inspections that are required by
AD 99–27–07, and retained in this
proposed AD, take about 2 work hours
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per airplane, at an average labor rate of
$65 per work hour. Based on these
figures, the estimated cost of the
currently required inspections is $130
per airplane, per inspection cycle.
The modification that is required by
AD 2004–23–08, and retained in this
proposed AD, takes about 2 work hours
per airplane, at an average labor rate of
$65 per work hour. Required parts will
cost about $9,620 per airplane. Based on
these figures, the estimated cost of the
currently required modification is
$9,750 per airplane.
The new proposed one-time
inspection would take about 1 work
hour per airplane, at an average labor
rate of $65 per work hour. Based on
these figures, the estimated cost of the
new inspection specified in this
proposed AD for U.S. operators is
$6,565 or $65 per airplane.
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.
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.
1. The authority citation for part 39
continues to read 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
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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
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13863 (69
FR 65528, November 15, 2004) and
adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2006–23760;
Directorate Identifier 2005–NM–211–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by March 6, 2006.
Affected ADs
(b) This AD supersedes AD 2004–23–08.
Applicability
(c) This AD applies to Airbus Model A300
B4–605R and B4–622R airplanes, and A300
F4–605R and F4–622R airplanes; certificated
in any category; on which Airbus
Modification 4801 has been accomplished;
except airplanes on which Airbus
Modification 12314 has been installed in
production.
Unsafe Condition
(d) This AD results from several reports
that the attachment bolts for the canisters,
modified by the requirements in the existing
AD, are too short and do not fully protrude
from the nuts. We are issuing this AD to
prevent damage to the fuel pump and fuel
pump canister, which could result in loss of
flame trap capability and could provide a
fuel ignition source in the center fuel tank.
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.
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5623
Restatement of Requirements of AD 2004–
23–08
A300–28–6061, Revision 04, dated August 1,
2002.
DEPARTMENT OF TRANSPORTATION
Inspections
(f) Prior to the accumulation of 5,000 total
hours’ time-in-service or within 250 hours’
time-in-service after February 8, 2000 (the
effective date of AD 99–27–07, (superseded
by AD 2004–23–08) amendment 39–11488),
whichever occurs later, perform a detailed
inspection for damage of the center tank fuel
pumps and fuel pump canisters, in
accordance with Airbus All Operators Telex
(AOT) 28–09, dated November 28, 1998.
Repeat the inspection prior to the
accumulation of 12,000 total hours’ time-inservice, or within 250 hours’ time-in-service
after accomplishment of the initial
inspection, whichever occurs later.
Thereafter, repeat the inspection at intervals
not to exceed 250 hours’ time-in-service,
until accomplishment of the initial
inspection required by paragraph (g) of this
AD.
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.’’
Modification
Federal Aviation Administration
(i) Within 18 months after December 20,
2004 (the effective date of AD 2004–23–08):
Modify the canisters of the center tank fuel
pumps (including an operational test) by
doing all the actions in accordance with
paragraphs 3.A., 3.B., 3.C., and 3.D. of the
Accomplishment Instructions of Airbus
Service Bulletin A300–28–6069, dated
September 4, 2001; Revision 01, dated May
28, 2002; or Revision 02, dated October 17,
2003. After the effective date of this AD,
Revision 02 of the service bulletin must be
used for accomplishing the modification.
Accomplishing this modification ends the
repetitive inspections required by paragraph
(g) of this AD.
14 CFR Part 39
hsrobinson on PROD1PC71 with PROPOSALS
(g) At the applicable time specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD:
Perform a detailed inspection to detect
damage of the center tank fuel pumps and
perform an eddy current inspection to detect
damage of the fuel pump canisters, in
accordance with Airbus Alert Service
Bulletin A300–28A6061, dated February 19,
1999; or Airbus Service Bulletin A300–28–
6061, Revision 04, dated August 1, 2002.
Repeat the inspections thereafter at intervals
not to exceed 1,500 flight cycles, until
accomplishment of paragraph (i) of this AD.
Accomplishment of the inspection required
by this paragraph constitutes terminating
action for the requirements of paragraph (f)
of this AD.
(1) For airplanes that have accumulated
11,000 or more total flight cycles as of
February 8, 2000: Inspect within 300 flight
cycles after February 8, 2000.
(2) For airplanes that have accumulated
8,500 or more total flight cycles, but fewer
than 11,000 total flight cycles, as of February
8, 2000: Inspect within 750 flight cycles after
February 8, 2000.
(3) For airplanes that have accumulated
fewer than 8,500 total flight cycles as of
February 8, 2000: Inspect prior to the
accumulation of 7,000 flight cycles, or within
1,500 flight cycles after February 8, 2000,
whichever occurs later.
Corrective Action
(h) If any damage is detected during any
inspection required by this AD, prior to
further flight, replace the damaged fuel pump
or fuel pump canister with a new or
serviceable part in accordance with Airbus
Alert Service Bulletin A300–28A6061, dated
February 19, 1999; or Airbus Service Bulletin
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New Requirements of This AD
One-Time Inspection/Replacement if
Necessary
(j) For airplanes on which Airbus Service
Bulletin A300–28–6069, dated September 4,
2001, or Revision 01, dated May 28, 2002,
has been accomplished before the effective
date of this AD: Within 18 months after the
effective date of this AD, perform a one-time
detailed inspection of the attachment bolts of
the outlet flange of the canisters of the center
tank fuel pumps for bolts that are too short
and do not protrude through the nut, and
replace the bolts as applicable, by doing all
the actions in accordance with paragraphs
3.A., 3.B., 3.C., 3.D., and 3.E. of the
Accomplishment Instructions of Airbus
Service Bulletin A300–28–6087, dated April
8, 2005. Do any applicable bolt replacement
before further flight.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) AMOCs approved previously in
accordance with AD 2004–23–08 are
approved as AMOCs for the corresponding
provisions of this AD.
Related Information
(l) French airworthiness directive F–2005–
147, dated August 17, 2005, also addresses
the subject of this AD.
Issued in Renton, Washington, on January
25, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–1418 Filed 2–1–06; 8:45 am]
BILLING CODE 4910–13–P
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[Docket No. FAA–2006–23762; Directorate
Identifier 2005–NM–226–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767 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 767 airplanes. This
proposed AD would require repetitive
inspections for cracking in the skin, the
bulkhead outer chord, and the strap of
the bulkhead outer chord at station
(STA) 1725.5; and repair if necessary.
This proposed AD also provides for
repairs, which are optional for airplanes
on which no cracking is found, that
terminate certain inspections. This
proposed AD results from reports of
cracking in the skin panel common to
stringer 7R and aft of the STA 1725.5
butt splice, and in the strap of the
bulkhead outer chord at STA 1725.5.
We are proposing this AD to detect and
correct cracking in the skin, the
bulkhead outer chord, or the strap of the
bulkhead outer chord in this area,
which could progress into surrounding
areas and result in reduced structural
integrity of the support structure for the
vertical or horizontal stabilizer and
subsequent loss of control of the
airplane.
We must receive comments on
this proposed AD by March 20, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
DATES:
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]]>Agencies
[Federal Register Volume 71, Number 22 (Thursday, February 2, 2006)]
[Proposed Rules]
[Pages 5620-5623]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-1418]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23760; Directorate Identifier 2005-NM-211-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600R and A300 F4-
600R Series 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 Airbus Model A300 B4-600R and
A300 F4-600R series airplanes. The existing AD requires repetitive
inspections for damage of the center tank fuel pumps and fuel pump
canisters and replacement of any damaged parts, and mandates
modification of the canisters of the center tank fuel pumps, which
terminates the repetitive inspections. For certain airplanes, this
proposed AD would require a one-time inspection of the attachment bolts
of the outlet flange of the canisters of the center tank fuel pumps for
bolts that are too short and do not protrude through the nut, and
replacement of the bolts if necessary. This proposed AD results from
several reports that the attachment bolts for the canisters, modified
by the requirements in the existing AD, are too short and do
[[Page 5621]]
not fully protrude from the nuts. We are proposing this AD to prevent
damage to the fuel pump and fuel pump canister, which could result in
loss of flame trap capability and could provide a fuel ignition source
in the center fuel tank.
DATES: We must receive comments on this proposed AD by March 6, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1622; fax (425) 227-1149.
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-2006-23760; Directorate Identifier 2005-NM-211-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 you
may visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
On November 1, 2004, we issued AD 2004-23-08, amendment 39-13863
(69 FR 65528, November 15, 2004), for certain Airbus Model A300 B4-600R
and A300 F4-600R series airplanes. That AD superseded AD 99-27-07,
amendment 39-11488 (65 FR 213, January 4, 2000), to mandate
modification of the canisters of the center tank fuel pumps, which
would terminate the repetitive inspections required by AD 99-27-07. AD
2004-23-08 resulted from the issuance of a new French airworthiness
directive, 2002-132(B), dated March 20, 2002, which mandated the
modification. We issued that AD to prevent damage to the fuel pump and
fuel pump canister, which could result in loss of flame trap capability
and could provide a fuel ignition source in the center fuel tank.
Actions Since Existing AD Was Issued
Since we issued AD 2004-23-08, the Direction Gonorale de l'Aviation
Civile (DGAC), which is the airworthiness authority for France, advises
that it has received several reports that the attachment bolts for the
canisters, modified by the requirements in the existing French AD, are
too short and do not fully protrude from the nuts. In light of these
findings, the DGAC has issued French airworthiness directive F-2005-
147, dated August 17, 2005. French airworthiness directive F-2005-147
adds a one-time inspection for bolts that are too short and do not
protrude from the nut, and replacement of the bolts if necessary.
Relevant Service Information
Airbus has issued Service Bulletin A300-28-6069, Revision 02, dated
October 17, 2003. For airplanes on which the modification specified in
the original issue or Revision 01 of the service bulletin has been
accomplished, Revision 02 includes additional work. That additional
work involves a one-time inspection of the attachment bolts of the
outlet flange of the canisters of the center tank fuel pumps for bolts
that are too short and do not protrude from the nut, and replacement of
the bolts if necessary.
Airbus has also issued Service Bulletin A300-28-6087, dated April
8, 2005, for airplanes on which Airbus Service Bulletin A300-28-6069,
dated September 4, 2001, or Revision 01, dated May 28, 2002, has been
accomplished. The service bulletin describes procedures for a one-time
inspection of the attachment bolts of the outlet flange of the
canisters of the center tank fuel pumps for bolts that are too short
and do not protrude from the nut, and replacement of the bolts if
necessary.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The DGAC mandated
the service information and issued French airworthiness directive F-
2005-147, dated August 17, 2005, to ensure the continued airworthiness
of these airplanes in France.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 2004-23-08 and would continue
to require repetitive inspections for damage of the center tank fuel
pumps and fuel pump canisters and replacement of any damaged parts, and
modification of the canisters of the center tank fuel pumps, which
terminates the repetitive inspections. For certain airplanes, this
proposed AD would also require a one-time
[[Page 5622]]
inspection of the attachment bolts of the outlet flange of the
canisters of the center tank fuel pumps for bolts that are too short
and do not protrude through the nut, and replacement of the bolts if
necessary.
Difference Between Proposed AD and French Airworthiness Directive
The applicability of the French airworthiness directive excludes
airplanes on which Airbus Service Bulletin A300-28-6069, Revision 2, or
A300-28-6087 were accomplished in service. However, we have not
excluded those airplanes in the applicability of this proposed AD;
rather, this proposed AD would include a requirement to accomplish the
actions specified in those service bulletins. This proposed requirement
would ensure that the actions specified in those service bulletins are
accomplished on all affected airplanes. Operators must continue to
operate the airplane in the configuration required by this proposed AD
unless an alternative method of compliance is approved.
Clarification of Inspection Terminology
In this proposed AD, the ``inspection'' specified in the service
bulletins is referred to as a ``detailed inspection.''
Change to Existing AD
This proposed AD would retain the requirements of the existing AD.
Since AD 2004-23-08 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
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Corresponding requirement
Requirement in AD 2004-23-08 in this proposed AD
------------------------------------------------------------------------
Paragraph (a)............................. Paragraph (f).
Paragraph (b)............................. Paragraph (g).
Paragraph (c)............................. Paragraph (h).
Paragraph (d)............................. Paragraph (i).
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Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Costs of Compliance
This proposed AD would affect about 101 airplanes of U.S. registry.
The inspections that are required by AD 99-27-07, and retained in
this proposed AD, take about 2 work hours per airplane, at an average
labor rate of $65 per work hour. Based on these figures, the estimated
cost of the currently required inspections is $130 per airplane, per
inspection cycle.
The modification that is required by AD 2004-23-08, and retained in
this proposed AD, takes about 2 work hours per airplane, at an average
labor rate of $65 per work hour. Required parts will cost about $9,620
per airplane. Based on these figures, the estimated cost of the
currently required modification is $9,750 per airplane.
The new proposed one-time inspection would take about 1 work hour
per airplane, at an average labor rate of $65 per work hour. Based on
these figures, the estimated cost of the new inspection specified in
this proposed AD for U.S. operators is $6,565 or $65 per airplane.
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 39-13863 (69 FR 65528, November 15, 2004) and adding
the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2006-23760; Directorate Identifier 2005-NM-
211-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by March 6,
2006.
Affected ADs
(b) This AD supersedes AD 2004-23-08.
Applicability
(c) This AD applies to Airbus Model A300 B4-605R and B4-622R
airplanes, and A300 F4-605R and F4-622R airplanes; certificated in
any category; on which Airbus Modification 4801 has been
accomplished; except airplanes on which Airbus Modification 12314
has been installed in production.
Unsafe Condition
(d) This AD results from several reports that the attachment
bolts for the canisters, modified by the requirements in the
existing AD, are too short and do not fully protrude from the nuts.
We are issuing this AD to prevent damage to the fuel pump and fuel
pump canister, which could result in loss of flame trap capability
and could provide a fuel ignition source in the center fuel tank.
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.
[[Page 5623]]
Restatement of Requirements of AD 2004-23-08
Inspections
(f) Prior to the accumulation of 5,000 total hours' time-in-
service or within 250 hours' time-in-service after February 8, 2000
(the effective date of AD 99-27-07, (superseded by AD 2004-23-08)
amendment 39-11488), whichever occurs later, perform a detailed
inspection for damage of the center tank fuel pumps and fuel pump
canisters, in accordance with Airbus All Operators Telex (AOT) 28-
09, dated November 28, 1998. Repeat the inspection prior to the
accumulation of 12,000 total hours' time-in-service, or within 250
hours' time-in-service after accomplishment of the initial
inspection, whichever occurs later. Thereafter, repeat the
inspection at intervals not to exceed 250 hours' time-in-service,
until accomplishment of the initial inspection required by paragraph
(g) of this AD.
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.''
(g) At the applicable time specified in paragraph (g)(1),
(g)(2), or (g)(3) of this AD: Perform a detailed inspection to
detect damage of the center tank fuel pumps and perform an eddy
current inspection to detect damage of the fuel pump canisters, in
accordance with Airbus Alert Service Bulletin A300-28A6061, dated
February 19, 1999; or Airbus Service Bulletin A300-28-6061, Revision
04, dated August 1, 2002. Repeat the inspections thereafter at
intervals not to exceed 1,500 flight cycles, until accomplishment of
paragraph (i) of this AD. Accomplishment of the inspection required
by this paragraph constitutes terminating action for the
requirements of paragraph (f) of this AD.
(1) For airplanes that have accumulated 11,000 or more total
flight cycles as of February 8, 2000: Inspect within 300 flight
cycles after February 8, 2000.
(2) For airplanes that have accumulated 8,500 or more total
flight cycles, but fewer than 11,000 total flight cycles, as of
February 8, 2000: Inspect within 750 flight cycles after February 8,
2000.
(3) For airplanes that have accumulated fewer than 8,500 total
flight cycles as of February 8, 2000: Inspect prior to the
accumulation of 7,000 flight cycles, or within 1,500 flight cycles
after February 8, 2000, whichever occurs later.
Corrective Action
(h) If any damage is detected during any inspection required by
this AD, prior to further flight, replace the damaged fuel pump or
fuel pump canister with a new or serviceable part in accordance with
Airbus Alert Service Bulletin A300-28A6061, dated February 19, 1999;
or Airbus Service Bulletin A300-28-6061, Revision 04, dated August
1, 2002.
Modification
(i) Within 18 months after December 20, 2004 (the effective date
of AD 2004-23-08): Modify the canisters of the center tank fuel
pumps (including an operational test) by doing all the actions in
accordance with paragraphs 3.A., 3.B., 3.C., and 3.D. of the
Accomplishment Instructions of Airbus Service Bulletin A300-28-6069,
dated September 4, 2001; Revision 01, dated May 28, 2002; or
Revision 02, dated October 17, 2003. After the effective date of
this AD, Revision 02 of the service bulletin must be used for
accomplishing the modification. Accomplishing this modification ends
the repetitive inspections required by paragraph (g) of this AD.
New Requirements of This AD
One-Time Inspection/Replacement if Necessary
(j) For airplanes on which Airbus Service Bulletin A300-28-6069,
dated September 4, 2001, or Revision 01, dated May 28, 2002, has
been accomplished before the effective date of this AD: Within 18
months after the effective date of this AD, perform a one-time
detailed inspection of the attachment bolts of the outlet flange of
the canisters of the center tank fuel pumps for bolts that are too
short and do not protrude through the nut, and replace the bolts as
applicable, by doing all the actions in accordance with paragraphs
3.A., 3.B., 3.C., 3.D., and 3.E. of the Accomplishment Instructions
of Airbus Service Bulletin A300-28-6087, dated April 8, 2005. Do any
applicable bolt replacement before further flight.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 2004-23-08
are approved as AMOCs for the corresponding provisions of this AD.
Related Information
(l) French airworthiness directive F-2005-147, dated August 17,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on January 25, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-1418 Filed 2-1-06; 8:45 am]
BILLING CODE 4910-13-P
