Airworthiness Directives; Airbus Model A300 B4 Series Airplanes; Model A300 B4-600 Series Airplanes; Model A300 C4-605R Variant F Airplanes; Model A310-200 Series Airplanes; and Model A310-300 Series Airplanes, 15079-15084 [E6-4407]
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Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules
not sooner than 24 months after the initial
inspection, perform a general visual
inspection of the flap structure and machined
ribs to detect corrosion, as specified in
paragraph (i)(1) or (i)(2), as applicable, in
accordance with the Accomplishment
Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.57–
066, Revision 2, dated March 18, 2004.
(1) If the corrosion extended into the boss
bores, or if it cannot be positively determined
from the records review specified in
paragraph (f) of this AD that corrosion did
not extend into the boss bores, do a flaps-off
inspection.
(2) If the corrosion did not extend into the
boss bores, do a flaps-on inspection.
Issued in Renton, Washington, on March
10, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–4411 Filed 3–24–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24200; Directorate
Identifier 2006–NM–012–AD]
Corrective Actions
RIN 2120–AA64
(j) If any corrosion is found during any
inspection required by this AD: Repair before
further flight in accordance with BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.57–066, Revision 2,
dated March 18, 2004, except as required by
paragraph (k) of this AD.
Airworthiness Directives; Airbus Model
A300 B4 Series Airplanes; Model A300
B4–600 Series Airplanes; Model A300
C4–605R Variant F Airplanes; Model
A310–200 Series Airplanes; and Model
A310–300 Series Airplanes
Exceptions to Service Bulletin Specifications
(k) If any corrosion is detected and BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.57–066, Revision 2,
dated March 18, 2004, specifies to contact the
manufacturer for repair instructions: Repair
before further flight, using a method
approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the Civil
Aviation Authority (or its delegated agent).
(l) Although the service bulletin referenced
in this AD specifies to submit certain
information to the manufacturer, this AD
does not include that requirement.
Credit
(m) Actions done before the effective date
of this AD in accordance with BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.57–066, dated May 15, 2001, or
Revision 1, dated September 20, 2002, are
acceptable for compliance with the
corresponding requirements of paragraph (g),
(h), (i), and (j) of this AD.
sroberts on PROD1PC70 with PROPOSALS
Alternative Methods of Compliance
(AMOCs)
(n)(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.
Related Information
(o) British airworthiness directive G–2005–
0018, dated July 20, 2005, also addresses the
subject of this AD.
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18:28 Mar 24, 2006
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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 B4–600 and A300
C4–600 series airplanes. The existing
AD currently requires a one-time
inspection to detect damage of the
pump diffuser guide slots (bayonet) of
the center tank fuel pumps, the pump
diffuser housings, and the pump
canisters; repetitive inspections to
detect damage of the fuel pumps and the
fuel pump canisters; and corrective
action, if necessary. This proposed AD
would add, for new airplanes, repetitive
inspections of the pump bodies for
cracking, damage, and missing and
broken fasteners; repetitive inspections
of the fuel pump canisters for a cracked
flange web; and corrective actions if
necessary. For all airplanes, this
proposed AD would also add
replacement of the fuel pump canisters
with new reinforced fuel pump
canisters, which ends the repetitive
inspections. This proposed AD results
from fuel system reviews conducted by
the manufacturer. We are proposing this
AD to detect and correct damage of the
center tank fuel pumps and fuel pump
canisters, which could result in
separation of a pump from its electrical
motor housing, loss of flame trap
capability, and a possible fuel ignition
source in the center fuel tank.
DATES: We must receive comments on
this proposed AD by April 26, 2006.
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15079
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:
ADDRESSES:
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–2006–24200;
Directorate Identifier 2006–NM–012–
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.
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Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules
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.
sroberts on PROD1PC70 with PROPOSALS
Discussion
On April 6, 2004, we issued AD 2004–
08–03, amendment 39–13572 (69 FR
19756, April 14, 2004), for certain
Airbus Model A300 B4–600 and A300
C4–600 series airplanes. That AD
requires a one-time inspection to detect
damage of the pump diffuser guide slots
(bayonet) of the center tank fuel pumps,
the pump diffuser housings, and the
pump canisters; repetitive inspections
to detect damage of the fuel pumps and
the fuel pump canisters; and corrective
action, if necessary. That AD resulted
from broken fuel tank pump canisters
found on Model A300 B4–600 and A300
C4–600 series airplanes. We issued that
AD to detect and correct damage of the
center tank fuel pumps and fuel pump
canisters, which could result in
separation of a pump from its electrical
motor housing, loss of flame trap
capability, and a possible fuel ignition
source in the center fuel tank.
Actions Since Existing AD Was Issued
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
we issued a regulation titled ‘‘Transport
Airplane Fuel Tank System Design
Review, Flammability Reduction and
Maintenance and Inspection
Requirements’’ (67 FR 23086, May 7,
2001). In addition to new airworthiness
standards for transport airplanes and
new maintenance requirements, this
rule included Special Federal Aviation
Regulation No. 88 (‘‘SFAR 88,’’
Amendment 21–78, and subsequent
Amendments 21–82 and 21–83).
Among other actions, SFAR 88
requires certain type design (i.e., type
certificate (TC) and supplemental type
certificate (STC)) holders to substantiate
that their fuel tank systems can prevent
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18:28 Mar 24, 2006
Jkt 208001
ignition sources in the fuel tanks. This
requirement applies to type design
holders for large turbine-powered
transport airplanes and for subsequent
modifications to those airplanes. It
requires them to perform design reviews
and to develop design changes and
maintenance procedures if their designs
do not meet the new fuel tank safety
standards. As explained in the preamble
to the rule, we intended to adopt
airworthiness directives to mandate any
changes found necessary to address
unsafe conditions identified as a result
of these reviews.
In evaluating these design reviews, we
have established four criteria intended
to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
which fuel tanks are exposed to
flammable conditions is one of these
criteria. The other three criteria address
the failure types under evaluation:
single failures, single failures in
combination with another latent
condition(s), and in-service failure
experience. For all four criteria, the
evaluations included consideration of
previous actions taken that may mitigate
the need for further action.
The Joint Aviation Authorities (JAA)
has issued a regulation that is similar to
SFAR 88. (The JAA is an associated
body of the European Civil Aviation
Conference (ECAC) representing the
civil aviation regulatory authorities of a
number of European States who have
agreed to co-operate in developing and
implementing common safety regulatory
standards and procedures.) Under this
regulation, the JAA stated that all
members of the ECAC that hold type
certificates for transport category
airplanes are required to conduct a
design review against explosion risks.
We have determined that the actions
identified in this AD are necessary to
reduce the potential of ignition sources
inside fuel tanks, which, in combination
with flammable fuel vapors, could result
in fuel tank explosions and consequent
loss of the airplane.
Since we issued AD 2004–08–03, the
´ ´
Direction Generale de l’Aviation Civile
(DGAC), which is the airworthiness
authority for France, has notified us that
the unsafe condition addressed in that
existing AD may also exist on Airbus
Model A300 B4 series airplanes and
Model A310–300 series airplanes.
Damage to the center tank fuel pumps
and fuel pump canisters, if not detected
and corrected, could result in separation
of a pump from its electrical motor
housing, loss of flame trap capability,
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Fmt 4702
Sfmt 4702
and a possible fuel ignition source in
the center fuel tank.
Additionally, in the notice of
proposed rulemaking (NPRM) (68 FR
70473, December 18, 2003) for AD
2004–08–03, we specified that the
actions required by AD 2004–08–03
were considered ‘‘interim action’’ and
that the manufacturer was developing a
modification to address the unsafe
condition. We indicated that we may
consider further rulemaking action once
the modification was developed,
approved, and available. The DGAC has
notified us that the manufacturer now
has developed such a modification. We
have determined that further
rulemaking action is indeed necessary;
this NPRM follows from that
determination.
Other Related Rulemaking
On January 26, 2006, we issued an
NPRM (71 FR 5620, February 2, 2006),
Docket No. FAA–2006–23760, that
proposes to supersede existing AD
2004–23–08, amendment 39–13863 (69
FR 65528, November 15, 2004). That
NPRM is applicable to certain Airbus
Model A300 B4–600R and A300 F4–
600R series airplanes. That NPRM
proposes to continue to require
repetitive inspections for damage of the
center tank fuel pumps and fuel pump
canisters and replacement of any
damaged parts, and to mandate
modification of the canisters of the
center tank fuel pumps, which
terminates the repetitive inspections.
For certain airplanes, that NPRM also
proposes to 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. We are proposing that NPRM
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, on certain Model
A300 B4–600R and A300 F4–600R
series airplanes equipped with a fuel
trim tank system. This proposed AD
addresses the same unsafe condition on
Model A300 B4–600R and A300 F4–
600R series airplanes not equipped with
a fuel trim tank system. That NPRM
does not affect the requirements of this
proposed AD.
Relevant Service Information
Airbus has issued the following
service information:
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Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules
Airbus airplanes
Airbus service information
Model A300 B4 series airplanes ........................
Service Bulletin A300–28–0084 .......................
Service Bulletin A300–28–0085 .......................
All Operators Telex (AOT) A300–600–
28A6075, Revision 01.
Service Bulletin A300–28–6089, Revision 01
Service Bulletin A310–28–2159 .......................
Service Bulletin A310–28–2160 .......................
Model A300 B4–600 series airplanes and
Model A300 C4–605R Variant F airplanes.
sroberts on PROD1PC70 with PROPOSALS
Model A310–200 and –300 series airplanes .....
Airbus Service Bulletins A300–28–
0084 and A310–28–2159 describe doing
the following procedures:
• A visual inspection in the area
between the impeller assembly and
inducer assembly of the fuel booster
pumps for cracks and missing or
damaged fasteners.
• A visual inspection in the area of
the guide slots (bayonet slots) of the fuel
booster pumps for signs of damage.
• If any crack or damage to a fuel
booster pump is found or if any fastener
is missing or damaged, replacement of
the pump with a new pump.
• A high frequency eddy current
(HFEC) inspection of the flange webs
inside the fuel pump canisters for
cracks.
• If any crack is found in the flange
webs of the fuel pump canisters,
replacement of the fuel pump canister
with a new fuel pump canister, or with
a new reinforced fuel pump canister in
accordance with Airbus Service Bulletin
A300–28–0085 or A310–28–2160, as
applicable.
Airbus AOT A300–600–28A6075,
Revision 01, describes doing the
following procedures:
• A one-time detailed visual
inspection to detect cracks, fretting, and
other damage of the lower part of the
pump diffuser guide slots (bayonet) of
the center tank fuel pumps and the
bottom of the pump diffuser housings;
and replacement of any damaged pump
and its corresponding fuel pump
canister with new parts.
• A one-time detailed inspection to
detect cracks of the center tank fuel
pump canisters, and replacement of any
cracked fuel pump canister and its
corresponding fuel pump with new
parts.
• Repetitive detailed visual
inspections to detect damage of the fuel
pumps, and replacement of any
damaged pump with a new part.
• Repetitive nondestructive test
(NDT) inspections to detect damage to
the fuel pump canisters, and
replacement of any damaged canister
with a new part. If a canister is replaced
with a new part, the next inspection
interval would be extended to 7,000
flight cycles, and thereafter repeated at
intervals of 3,000 flight cycles. (The
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18:28 Mar 24, 2006
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original issue of AOT A300–600–
28A6075, dated February 20, 2003, and
AD 2004–08–03 specify a repetitive
inspection interval of 1,500 flight
cycles.) Replacement of a canister ends
the repetitive inspections of the fuel
pumps.
• A report of inspection findings.
Airbus AOT A300–600–28A6075
refers to Airbus Alert Service Bulletin
A300–28A6061, Revision 04, dated
August 1, 2002, and the A300–600
Nondestructive Testing Manual (NTM)
57–10–14 as additional sources of
service information for accomplishing
the NDT inspections.
Airbus Service Bulletins A300–28–
0085, A300–28–6089, and A310–28–
2160 describe procedures for replacing
the fuel pump canisters with new
reinforced fuel pump canisters.
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–2005–199,
dated December 7, 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 2004–08–03 and would retain the
requirements of the existing AD and
extend the repetitive interval for certain
eddy current inspections. This proposed
AD would also require, for certain
airplanes, repetitive detailed
inspections of the pump bodies for
cracking, damage, and missing and
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15081
Date
June 28, 2005.
July 18, 2005.
October 24, 2005.
November 28, 2005.
June 28, 2005.
July 18, 2005.
broken fasteners; repetitive HFEC
inspections of the fuel pump canisters
for a cracked flange web; and corrective
actions if necessary. This proposed AD
would also require, for all airplanes,
replacement of the fuel pump canisters
with new reinforced canisters. This
proposed AD also contains differences
with the French airworthiness directive
F–2005–199, as discussed under
‘‘Differences Between the NPRM and
French Airworthiness Directive.’’
Differences Between the NPRM and
French Airworthiness Directive
The applicability of French
airworthiness directive F–2005–199
excludes the following airplanes:
• Model A300 B4–600 series
airplanes and Model A300 C4–600
series airplanes, manufacturer serial
numbers 546, 553, 618, and 623, on
which Airbus Service Bulletin A300–
28–6082 has been accomplished in
service.
• Model A300 B4–600 series
airplanes and Model A300 C4–600
series airplanes on which Airbus
Service Bulletin A300–28–6089 has
been accomplished in service.
• Model A300 series airplanes on
which Airbus A300–28–0085 has been
accomplished in service.
• Model A310 series airplanes on
which Airbus Service Bulletin A310–
28–2160 has been accomplished in
service.
However, we have not excluded those
airplanes in the applicability of this
NPRM; rather, this NPRM includes a
requirement to accomplish the actions
specified in those service bulletins. This
requirement would ensure that the
actions specified in the service bulletins
and required by this NPRM are
accomplished on all affected airplanes.
Operators must continue to operate the
airplane in the configuration required
by this NPRM unless an alternative
method of compliance is approved. This
difference has been coordinated with
the DGAC.
The applicability of French
airworthiness directive F–2005–199 also
excludes all Airbus Model A300B2–100,
–200, and –300 airplanes, and includes
all Airbus A300–600ST airplanes except
those on which Airbus Service Bulletin
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A300–28–2160 has been accomplished
in service. However, we have not
referenced any of these airplanes in the
applicability of this NPRM, since these
airplanes are not type certificated in the
U.S.
AD 2004–08–03 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 NPRM,
as listed in the following table:
Clarification of Inspection Terminology
REVISED PARAGRAPH IDENTIFIERS
The ‘‘detailed visual inspection’’
specified in French airworthiness
directive F–2005–199 and in the
referenced service information is
referred to as a ‘‘detailed inspection’’ in
this NPRM. We have updated the
definition of a ‘‘detailed inspection’’ in
Note 1 of this NPRM.
Changes to Existing AD
This NPRM would retain all
requirements of AD 2004–08–03. Since
Corresponding requirement in this
NPRM
Requirement in AD
2004–08–03
Paragraph
Paragraph
Paragraph
Paragraph
(a)
(b)
(c)
(d)
............
............
............
............
Paragraph
Paragraph
Paragraph
Paragraph
recent type certificate data sheet for the
affected models.
Note 2 of AD 2004–08–03 incorrectly
references paragraph (b)(2) of that AD. We
have revised this NPRM to reference
paragraphs (g) and (h).
We have increased the repetitive
interval to 3,000 flight cycles for the
eddy current inspections in paragraph
(g) and (h) of this NPRM to correspond
with French airworthiness directive F–
2005–199.
Costs of Compliance
(f)
(g)
(h)
(i)
This proposed AD would affect about
74 airplanes of U.S. registry. The
following table provides the estimated
costs, at an average labor rate of $80 per
hour, for U.S. operators to comply with
this proposed AD.
We have revised the applicability of
the NPRM to identify model
designations as published in the most
ESTIMATED COSTS
Airbus model
Action
A300 B4–600 series airplanes and
Model A300 C4–605R Variant F airplanes.
Detailed inspection (required
by AD 2004–
08–03).
Eddy current inspection (required by AD
2004–08–03).
Replacements
(new proposed action).
Repetitive inspections
(new proposed action).
Replacements
(new proposed action).
Repetitive inspections
(new proposed action).
Replacements
(new proposed action).
A300 B4 series airplanes ....................
A310–200 and –300 series airplanes
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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
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Cost per airplane
2
None .................
$160 ..................
2
$320.
5
None .................
$400, per inspection cycle.
2
$800, per inspection
cycle.
7
$70 ....................
$630 ..................
2
$1,260.
2
None .................
$160, per inspection cycle.
16
$2,560, per inspection
cycle.
10
$80 ....................
$880 ..................
16
$14,080.
2
None .................
$160, per inspection cycle.
56
$8,960, per inspection
cycle.
10
$50 ....................
$850 ..................
56
$47,600.
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
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Number of
U.S.-registered airplanes
Parts
Work hours
Fmt 4702
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Fleet cost
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
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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 39–13572 (69
FR 19756, April 14, 2004) and adding
the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2006–24200;
Directorate Identifier 2006–NM–012–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by April 26, 2006.
Affected ADs
(b) This AD supersedes AD 2004–08–03.
Applicability
(c) This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) and (c)(2) of
this AD, certificated in any category.
(1) Model A300 B4–601, B4–603, B4–620,
and B4–622 airplanes; and Model A300 C4–
605R Variant F airplanes; except those
airplanes equipped with a fuel trim tank
system (that have incorporated Airbus
Modification 4801).
(2) All Model A300 B4–2C, B4–103, and
B4–203 airplanes; Model A310–203, –204,
–221, and –222 airplanes; and Model A310–
304, –322, –324, and –325 airplanes.
sroberts on PROD1PC70 with PROPOSALS
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to detect and correct
damage of the center tank fuel pumps and
fuel pump canisters, which could result in
separation of a pump from its electrical
motor housing, loss of flame trap capability,
and a possible 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.
VerDate Aug<31>2005
18:28 Mar 24, 2006
Jkt 208001
Restatement of Requirements of AD 2004–
08–03
Detailed Inspections
(f) For Model A300 B4–601, B4–603, B4–
620, and B4–622 airplanes and Model A300
C4–605R Variant F airplanes: Within 15 days
after May 19, 2004 (the effective date of AD
2004–08–03) (unless accomplished
previously), perform detailed inspections as
specified in paragraphs (f)(1) and (f)(2) of this
AD, in accordance with paragraph 4.2 of
Airbus All Operators Telex (AOT) A300–
600–28A6075, dated February 20, 2003; or
Revision 01, dated October 24, 2005.
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.’’
(1) Inspect the lower part of the pump
diffuser guide slots (bayonet) of the center
tank fuel pumps and the bottom of the pump
diffuser housings to detect cracks, fretting,
and other damage. Replace any damaged
pump and the corresponding fuel pump
canister with new parts before further flight
in accordance with the AOT.
(2) Inspect the center tank fuel pump
canisters to detect cracks. Replace any
cracked fuel pump canister and the
corresponding fuel pump with new parts
before further flight in accordance with the
AOT.
Repetitive Inspections With New Repetitive
Intervals
(g) For Model A300 B4–601, B4–603, B4–
620, and B4–622 airplanes and Model A300
C4–605R Variant F airplanes: Within 600
flight hours after May 19, 2004, perform a
detailed inspection of the fuel pumps, and an
eddy current inspection of the fuel pump
canisters, to detect damage. Do the
inspections in accordance with paragraph 4.3
of Airbus AOT A300–600–28A6075, dated
February 20, 2003; or Revision 01, dated
October 24, 2005. Replace any damaged part
with a new part before further flight in
accordance with the AOT. Repeat the
inspections at intervals not to exceed 3,000
flight cycles.
(h) For Model A300 B4–601, B4–603, B4–
620, and B4–622 airplanes and Model A300
C4–605R Variant F airplanes: Within 7,000
flight cycles after canister replacement as
specified in paragraph (g) of this AD, perform
an eddy current inspection of the fuel pump
canisters to detect damage in accordance
with Airbus AOT A300–600–28A6075, dated
February 20, 2003; or Revision 01, dated
October 24, 2005. Replace any damaged part
with a new part before further flight in
accordance with the AOT. Thereafter repeat
the inspection at intervals not to exceed
3,000 flight cycles.
Note 2: Airbus AOT A300–600–28A6075
refers to Airbus Alert Service Bulletin A300–
28A6061, Revision 04, dated August 1, 2002,
as an additional source of service information
PO 00000
Frm 00037
Fmt 4702
Sfmt 4702
15083
for accomplishment of the eddy current
inspection required by paragraphs (g) and (h)
of this AD.
Reporting Requirement
(i) For Model A300 B4–601, B4–603, B4–
620, and B4–622 airplanes and Model A300
C4–605R Variant F airplanes: At the
applicable time specified in paragraph (i)(1)
or (i)(2) of this AD, submit a report of
findings (both positive and negative) of each
inspection required by this AD, in
accordance with Airbus AOT A300–600–
28A6075, dated February 20, 2003.
Information collection requirements
contained in this AD have been approved by
the Office of Management and Budget (OMB)
under the provisions of the Paperwork
Reduction Act of 1980 (44 U.S.C. 3501 et
seq.) and have been assigned OMB Control
Number 2120–0056.
(1) For any inspection accomplished after
May 19, 2004: Submit the report within 10
days after performing that inspection.
(2) For any inspection accomplished before
May 19, 2004: Submit the report within 10
days after May 19, 2004.
Requirements of This AD
Repetitive Inspections for New Airplanes
(j) For Model A300 B4–2C, B4–103, and
B4–203 airplanes; Model A310–203, –204,
–221, and –222 airplanes; and Model A310–
304, –322, –324, and –325 airplanes: At the
applicable compliance time specified in
paragraphs (j)(1) and (j)(2) of this AD, do a
detailed inspection of the pump bodies for
cracking, damage, and missing and broken
fasteners; and do a high frequency eddy
current (HFEC) inspection of the fuel pump
canisters for a cracked flange web, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
28–0084, dated June 28, 2005 (for Model
A300 B4–2C, B4–103, and B4–203 airplanes);
or Airbus Service Bulletin A310–28–2159,
dated June 28, 2005 (for Model A310–203,
–204, –221, and –222 airplanes and Model
A310–304, –322, –324, and –325 airplanes),
as applicable. If any crack or damage to the
pump bodies is found or any missing or
broken fastener is found, before further flight,
replace the fuel pump with a new fuel pump
in accordance with the applicable service
bulletin. Repeat the detailed inspection of the
pump bodies thereafter at intervals not to
exceed 3,000 flight cycles. If no cracked
flange web is found, repeat the HFEC
inspection of the fuel pump canisters
thereafter at intervals not to exceed 3,000
flight cycles. Accomplishing the
replacements specified in paragraph (l) of
this AD terminates the repetitive detailed and
HFEC inspections.
(1) For Model A300 B4–2C, B4–103, and
B4–203 airplanes: Inspect before the airplane
has accumulated 19,600 total flight cycles, or
within 1,000 flight cycles after the effective
date of this AD, whichever is later.
(2) For Model A310–203, –204, –221, and
–222 airplanes and Model A310–304, –322,
–324, and –325 airplanes: Inspect before the
airplane has accumulated 27,000 total flight
cycles, or within 1,000 flight cycles after the
effective date of this AD, whichever is later.
E:\FR\FM\27MRP1.SGM
27MRP1
15084
Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules
Corrective Action for Cracked Flange Web
(k) For Model A300 B4–2C, B4–103, and
B4–203; Model A310–203, –204, –221, and
–222 airplanes; and Model A310–304, –322,
–324, and –325 airplanes: If any flange web
is found cracked during any HFEC inspection
required by paragraph (j) of this AD, before
further flight after the inspection, replace the
fuel pump canister with a new fuel pump
canister in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–28–0084, dated June
28, 2005; or Airbus Service Bulletin A310–
28–2159, dated June 28, 2005, as applicable.
Repeat the HFEC inspection at the applicable
compliance times specified in paragraph
(k)(1) or (k)(2) of this AD, until the
replacements specified in paragraph (l) of
this AD are accomplished.
(1) For Model A300 B4–2C, B4–103, and
B4–203 airplanes: Inspect within 19,600
flight cycles after replacing the fuel pump
canisters and thereafter at intervals not to
exceed 3,000 flight cycles.
(2) For Model A310–203, –204, –221, and
–222 airplanes and Model A310–304, –322,
–324, and –325 airplanes: Inspect within
27,000 flight cycles after replacing the fuel
pump canisters and thereafter at intervals not
to exceed 3,000 flight cycles.
Terminating Action: Replacement of Fuel
Pump Canisters
(l) For all airplanes: Within 66 months after
the effective date of this AD, replace the fuel
pump canisters with new reinforced fuel
pump canisters, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–28–0085, dated July
18, 2005 (for Model A300 B4–2C, B4–103,
and B4–203 airplanes); Airbus Service
Bulletin A300–28–6089, Revision 01, dated
November 28, 2005 (for Model A300 B4–601,
B4–603, B4–620, and B4–622 airplanes and
Model A300 C4–605R Variant F airplanes); or
Airbus Service Bulletin A310–28–2160,
dated July 18, 2005 (for Model A310–203,
–204, –221, and –222 airplanes and Model
A310–304, –322, –324, and –325 airplanes),
as applicable. Replacement of a fuel pump
canister terminates the repetitive inspections
required by paragraphs (f), (g), (h), (j) and (k),
as applicable, for that fuel pump canister
only.
sroberts on PROD1PC70 with PROPOSALS
Credit for Previous Service Bulletin
(m) For Model A300 B4–601, B4–603, B4–
620, and B4–622 airplanes and Model A300
C4–605R Variant F airplanes: Actions done
before the effective date of this AD in
accordance with Airbus Service Bulletin
A300–28–6089, dated July 18, 2005, are
acceptable for compliance with the
requirements of paragraph (l) of this AD.
Alternative Methods of Compliance (AMOCs)
(n)(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.
VerDate Aug<31>2005
20:57 Mar 24, 2006
Jkt 208001
Related Information
(o) French airworthiness directive F–2005–
199, dated December 7, 2005, also addresses
the subject of this AD.
Issued in Renton, Washington, on March
10, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–4407 Filed 3–24–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19566; Directorate
Identifier 2004–NM–72–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B2 and A300 B4 Series Airplanes;
and Model A300 B4–600, B4–600R, and
F4–600R Series Airplanes, and Model
C4–605R Variant F Airplanes
(Collectively Called A300–600 Series
Airplanes)
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
SUMMARY: The FAA is revising an earlier
supplemental NPRM for an
airworthiness directive (AD) that
applies to certain Airbus airplanes as
listed above. The first supplemental
NPRM would have required repetitively
inspecting for cracking in the web of
nose rib 7 of the inner flap on the wings,
and performing related investigative/
corrective actions if necessary. The
original NPRM resulted from reports of
cracking in the web of nose rib 7 of the
inner flap. This action revises the first
supplemental NPRM by requiring
eventual replacement of nose rib 7 with
a new, improved rib, which would
terminate the proposed inspections.
This action also removes from the
applicability airplanes on which the
improved nose rib 7 was installed
during production. We are proposing
this supplemental NPRM to prevent
cracking in the web of nose rib 7, which
could result in rupture of the
attachment fitting between the inner
flap and flap track 2, and consequent
reduced structural integrity of the flap.
DATES: We must receive comments on
this supplemental NPRM by April 21,
2006.
PO 00000
Frm 00038
Fmt 4702
Sfmt 4702
Use one of the following
addresses to submit comments on this
supplemental NPRM.
• 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:
ADDRESSES:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this supplemental NPRM.
Send your comments to an address
listed in the ADDRESSES section. Include
the docket number ‘‘Docket No. FAA–
2004–19566; Directorate Identifier
2004–NM–72–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this supplemental NPRM. We
will consider all comments received by
the closing date and may amend this
supplemental NPRM in light of those
comments.
We will post all comments submitted,
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 supplemental NPRM. 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.
E:\FR\FM\27MRP1.SGM
27MRP1
]]>Agencies
[Federal Register Volume 71, Number 58 (Monday, March 27, 2006)]
[Proposed Rules]
[Pages 15079-15084]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-4407]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24200; Directorate Identifier 2006-NM-012-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4 Series Airplanes;
Model A300 B4-600 Series Airplanes; Model A300 C4-605R Variant F
Airplanes; Model A310-200 Series Airplanes; and Model A310-300 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Airbus Model A300 B4-600 and
A300 C4-600 series airplanes. The existing AD currently requires a one-
time inspection to detect damage of the pump diffuser guide slots
(bayonet) of the center tank fuel pumps, the pump diffuser housings,
and the pump canisters; repetitive inspections to detect damage of the
fuel pumps and the fuel pump canisters; and corrective action, if
necessary. This proposed AD would add, for new airplanes, repetitive
inspections of the pump bodies for cracking, damage, and missing and
broken fasteners; repetitive inspections of the fuel pump canisters for
a cracked flange web; and corrective actions if necessary. For all
airplanes, this proposed AD would also add replacement of the fuel pump
canisters with new reinforced fuel pump canisters, which ends the
repetitive inspections. This proposed AD results from fuel system
reviews conducted by the manufacturer. We are proposing this AD to
detect and correct damage of the center tank fuel pumps and fuel pump
canisters, which could result in separation of a pump from its
electrical motor housing, loss of flame trap capability, and a possible
fuel ignition source in the center fuel tank.
DATES: We must receive comments on this proposed AD by April 26, 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-2006-24200; Directorate Identifier 2006-NM-012-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.
[[Page 15080]]
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 April 6, 2004, we issued AD 2004-08-03, amendment 39-13572 (69
FR 19756, April 14, 2004), for certain Airbus Model A300 B4-600 and
A300 C4-600 series airplanes. That AD requires a one-time inspection to
detect damage of the pump diffuser guide slots (bayonet) of the center
tank fuel pumps, the pump diffuser housings, and the pump canisters;
repetitive inspections to detect damage of the fuel pumps and the fuel
pump canisters; and corrective action, if necessary. That AD resulted
from broken fuel tank pump canisters found on Model A300 B4-600 and
A300 C4-600 series airplanes. We issued that AD to detect and correct
damage of the center tank fuel pumps and fuel pump canisters, which
could result in separation of a pump from its electrical motor housing,
loss of flame trap capability, and a possible fuel ignition source in
the center fuel tank.
Actions Since Existing AD Was Issued
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(67 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, single failures in
combination with another latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
The Joint Aviation Authorities (JAA) has issued a regulation that
is similar to SFAR 88. (The JAA is an associated body of the European
Civil Aviation Conference (ECAC) representing the civil aviation
regulatory authorities of a number of European States who have agreed
to co-operate in developing and implementing common safety regulatory
standards and procedures.) Under this regulation, the JAA stated that
all members of the ECAC that hold type certificates for transport
category airplanes are required to conduct a design review against
explosion risks.
We have determined that the actions identified in this AD are
necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in fuel tank explosions and consequent loss of the airplane.
Since we issued AD 2004-08-03, the Direction G[eacute]n[eacute]rale
de l'Aviation Civile (DGAC), which is the airworthiness authority for
France, has notified us that the unsafe condition addressed in that
existing AD may also exist on Airbus Model A300 B4 series airplanes and
Model A310-300 series airplanes. Damage to the center tank fuel pumps
and fuel pump canisters, if not detected and corrected, could result in
separation of a pump from its electrical motor housing, loss of flame
trap capability, and a possible fuel ignition source in the center fuel
tank.
Additionally, in the notice of proposed rulemaking (NPRM) (68 FR
70473, December 18, 2003) for AD 2004-08-03, we specified that the
actions required by AD 2004-08-03 were considered ``interim action''
and that the manufacturer was developing a modification to address the
unsafe condition. We indicated that we may consider further rulemaking
action once the modification was developed, approved, and available.
The DGAC has notified us that the manufacturer now has developed such a
modification. We have determined that further rulemaking action is
indeed necessary; this NPRM follows from that determination.
Other Related Rulemaking
On January 26, 2006, we issued an NPRM (71 FR 5620, February 2,
2006), Docket No. FAA-2006-23760, that proposes to supersede existing
AD 2004-23-08, amendment 39-13863 (69 FR 65528, November 15, 2004).
That NPRM is applicable to certain Airbus Model A300 B4-600R and A300
F4-600R series airplanes. That NPRM proposes to continue to require
repetitive inspections for damage of the center tank fuel pumps and
fuel pump canisters and replacement of any damaged parts, and to
mandate modification of the canisters of the center tank fuel pumps,
which terminates the repetitive inspections. For certain airplanes,
that NPRM also proposes to 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. We are
proposing that NPRM 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, on certain
Model A300 B4-600R and A300 F4-600R series airplanes equipped with a
fuel trim tank system. This proposed AD addresses the same unsafe
condition on Model A300 B4-600R and A300 F4-600R series airplanes not
equipped with a fuel trim tank system. That NPRM does not affect the
requirements of this proposed AD.
Relevant Service Information
Airbus has issued the following service information:
[[Page 15081]]
------------------------------------------------------------------------
Airbus service
Airbus airplanes information Date
------------------------------------------------------------------------
Model A300 B4 series Service Bulletin June 28, 2005.
airplanes. A300-28-0084.
Service Bulletin July 18, 2005.
A300-28-0085.
Model A300 B4-600 series All Operators Telex October 24, 2005.
airplanes and Model A300 C4- (AOT) A300-600-
605R Variant F airplanes. 28A6075, Revision
01.
Service Bulletin November 28, 2005.
A300-28-6089,
Revision 01.
Model A310-200 and -300 Service Bulletin June 28, 2005.
series airplanes. A310-28-2159.
Service Bulletin July 18, 2005.
A310-28-2160.
------------------------------------------------------------------------
Airbus Service Bulletins A300-28-0084 and A310-28-2159 describe
doing the following procedures:
A visual inspection in the area between the impeller
assembly and inducer assembly of the fuel booster pumps for cracks and
missing or damaged fasteners.
A visual inspection in the area of the guide slots
(bayonet slots) of the fuel booster pumps for signs of damage.
If any crack or damage to a fuel booster pump is found or
if any fastener is missing or damaged, replacement of the pump with a
new pump.
A high frequency eddy current (HFEC) inspection of the
flange webs inside the fuel pump canisters for cracks.
If any crack is found in the flange webs of the fuel pump
canisters, replacement of the fuel pump canister with a new fuel pump
canister, or with a new reinforced fuel pump canister in accordance
with Airbus Service Bulletin A300-28-0085 or A310-28-2160, as
applicable.
Airbus AOT A300-600-28A6075, Revision 01, describes doing the
following procedures:
A one-time detailed visual inspection to detect cracks,
fretting, and other damage of the lower part of the pump diffuser guide
slots (bayonet) of the center tank fuel pumps and the bottom of the
pump diffuser housings; and replacement of any damaged pump and its
corresponding fuel pump canister with new parts.
A one-time detailed inspection to detect cracks of the
center tank fuel pump canisters, and replacement of any cracked fuel
pump canister and its corresponding fuel pump with new parts.
Repetitive detailed visual inspections to detect damage of
the fuel pumps, and replacement of any damaged pump with a new part.
Repetitive nondestructive test (NDT) inspections to detect
damage to the fuel pump canisters, and replacement of any damaged
canister with a new part. If a canister is replaced with a new part,
the next inspection interval would be extended to 7,000 flight cycles,
and thereafter repeated at intervals of 3,000 flight cycles. (The
original issue of AOT A300-600-28A6075, dated February 20, 2003, and AD
2004-08-03 specify a repetitive inspection interval of 1,500 flight
cycles.) Replacement of a canister ends the repetitive inspections of
the fuel pumps.
A report of inspection findings.
Airbus AOT A300-600-28A6075 refers to Airbus Alert Service Bulletin
A300-28A6061, Revision 04, dated August 1, 2002, and the A300-600
Nondestructive Testing Manual (NTM) 57-10-14 as additional sources of
service information for accomplishing the NDT inspections.
Airbus Service Bulletins A300-28-0085, A300-28-6089, and A310-28-
2160 describe procedures for replacing the fuel pump canisters with new
reinforced fuel pump canisters. 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-2005-199, dated December 7, 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 2004-08-03 and would retain the
requirements of the existing AD and extend the repetitive interval for
certain eddy current inspections. This proposed AD would also require,
for certain airplanes, repetitive detailed inspections of the pump
bodies for cracking, damage, and missing and broken fasteners;
repetitive HFEC inspections of the fuel pump canisters for a cracked
flange web; and corrective actions if necessary. This proposed AD would
also require, for all airplanes, replacement of the fuel pump canisters
with new reinforced canisters. This proposed AD also contains
differences with the French airworthiness directive F-2005-199, as
discussed under ``Differences Between the NPRM and French Airworthiness
Directive.''
Differences Between the NPRM and French Airworthiness Directive
The applicability of French airworthiness directive F-2005-199
excludes the following airplanes:
Model A300 B4-600 series airplanes and Model A300 C4-600
series airplanes, manufacturer serial numbers 546, 553, 618, and 623,
on which Airbus Service Bulletin A300-28-6082 has been accomplished in
service.
Model A300 B4-600 series airplanes and Model A300 C4-600
series airplanes on which Airbus Service Bulletin A300-28-6089 has been
accomplished in service.
Model A300 series airplanes on which Airbus A300-28-0085
has been accomplished in service.
Model A310 series airplanes on which Airbus Service
Bulletin A310-28-2160 has been accomplished in service.
However, we have not excluded those airplanes in the applicability
of this NPRM; rather, this NPRM includes a requirement to accomplish
the actions specified in those service bulletins. This requirement
would ensure that the actions specified in the service bulletins and
required by this NPRM are accomplished on all affected airplanes.
Operators must continue to operate the airplane in the configuration
required by this NPRM unless an alternative method of compliance is
approved. This difference has been coordinated with the DGAC.
The applicability of French airworthiness directive F-2005-199 also
excludes all Airbus Model A300B2-100, -200, and -300 airplanes, and
includes all Airbus A300-600ST airplanes except those on which Airbus
Service Bulletin
[[Page 15082]]
A300-28-2160 has been accomplished in service. However, we have not
referenced any of these airplanes in the applicability of this NPRM,
since these airplanes are not type certificated in the U.S.
Clarification of Inspection Terminology
The ``detailed visual inspection'' specified in French
airworthiness directive F-2005-199 and in the referenced service
information is referred to as a ``detailed inspection'' in this NPRM.
We have updated the definition of a ``detailed inspection'' in Note 1
of this NPRM.
Changes to Existing AD
This NPRM would retain all requirements of AD 2004-08-03. Since AD
2004-08-03 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 NPRM, as listed in the
following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2004-08-03 this NPRM
------------------------------------------------------------------------
Paragraph (a)............................. Paragraph (f)
Paragraph (b)............................. Paragraph (g)
Paragraph (c)............................. Paragraph (h)
Paragraph (d)............................. Paragraph (i)
------------------------------------------------------------------------
We have revised the applicability of the NPRM to identify model
designations as published in the most recent type certificate data
sheet for the affected models.
Note 2 of AD 2004-08-03 incorrectly references paragraph (b)(2)
of that AD. We have revised this NPRM to reference paragraphs (g)
and (h).
We have increased the repetitive interval to 3,000 flight cycles
for the eddy current inspections in paragraph (g) and (h) of this NPRM
to correspond with French airworthiness directive F-2005-199.
Costs of Compliance
This proposed AD would affect about 74 airplanes of U.S. registry.
The following table provides the estimated costs, at an average labor
rate of $80 per hour, for U.S. operators to comply with this proposed
AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
U.S.-
Airbus model Action Work hours Parts Cost per airplane registered Fleet cost
airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
A300 B4-600 series airplanes and Detailed inspection 2 None................. $160................. 2 $320.
Model A300 C4-605R Variant F (required by AD 2004-
airplanes. 08-03).
Eddy current 5 None................. $400, per inspection 2 $800, per inspection
inspection (required cycle. cycle.
by AD 2004-08-03).
Replacements (new 7 $70.................. $630................. 2 $1,260.
proposed action).
A300 B4 series airplanes.......... Repetitive 2 None................. $160, per inspection 16 $2,560, per
inspections (new cycle. inspection cycle.
proposed action).
Replacements (new 10 $80.................. $880................. 16 $14,080.
proposed action).
A310-200 and -300 series airplanes Repetitive 2 None................. $160, per inspection 56 $8,960, per
inspections (new cycle. inspection cycle.
proposed action).
Replacements (new 10 $50.................. $850................. 56 $47,600.
proposed action).
--------------------------------------------------------------------------------------------------------------------------------------------------------
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
[[Page 15083]]
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 39-13572 (69 FR 19756, April 14, 2004) and adding
the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2006-24200; Directorate Identifier 2006-NM-
012-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 26,
2006.
Affected ADs
(b) This AD supersedes AD 2004-08-03.
Applicability
(c) This AD applies to the Airbus airplanes identified in
paragraphs (c)(1) and (c)(2) of this AD, certificated in any
category.
(1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; and
Model A300 C4-605R Variant F airplanes; except those airplanes
equipped with a fuel trim tank system (that have incorporated Airbus
Modification 4801).
(2) All Model A300 B4-2C, B4-103, and B4-203 airplanes; Model
A310-203, -204, -221, and -222 airplanes; and Model A310-304, -322,
-324, and -325 airplanes.
Unsafe Condition
(d) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to detect and correct damage of
the center tank fuel pumps and fuel pump canisters, which could
result in separation of a pump from its electrical motor housing,
loss of flame trap capability, and a possible 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.
Restatement of Requirements of AD 2004-08-03
Detailed Inspections
(f) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes
and Model A300 C4-605R Variant F airplanes: Within 15 days after May
19, 2004 (the effective date of AD 2004-08-03) (unless accomplished
previously), perform detailed inspections as specified in paragraphs
(f)(1) and (f)(2) of this AD, in accordance with paragraph 4.2 of
Airbus All Operators Telex (AOT) A300-600-28A6075, dated February
20, 2003; or Revision 01, dated October 24, 2005.
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.''
(1) Inspect the lower part of the pump diffuser guide slots
(bayonet) of the center tank fuel pumps and the bottom of the pump
diffuser housings to detect cracks, fretting, and other damage.
Replace any damaged pump and the corresponding fuel pump canister
with new parts before further flight in accordance with the AOT.
(2) Inspect the center tank fuel pump canisters to detect
cracks. Replace any cracked fuel pump canister and the corresponding
fuel pump with new parts before further flight in accordance with
the AOT.
Repetitive Inspections With New Repetitive Intervals
(g) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes
and Model A300 C4-605R Variant F airplanes: Within 600 flight hours
after May 19, 2004, perform a detailed inspection of the fuel pumps,
and an eddy current inspection of the fuel pump canisters, to detect
damage. Do the inspections in accordance with paragraph 4.3 of
Airbus AOT A300-600-28A6075, dated February 20, 2003; or Revision
01, dated October 24, 2005. Replace any damaged part with a new part
before further flight in accordance with the AOT. Repeat the
inspections at intervals not to exceed 3,000 flight cycles.
(h) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes
and Model A300 C4-605R Variant F airplanes: Within 7,000 flight
cycles after canister replacement as specified in paragraph (g) of
this AD, perform an eddy current inspection of the fuel pump
canisters to detect damage in accordance with Airbus AOT A300-600-
28A6075, dated February 20, 2003; or Revision 01, dated October 24,
2005. Replace any damaged part with a new part before further flight
in accordance with the AOT. Thereafter repeat the inspection at
intervals not to exceed 3,000 flight cycles.
Note 2: Airbus AOT A300-600-28A6075 refers to Airbus Alert
Service Bulletin A300-28A6061, Revision 04, dated August 1, 2002, as
an additional source of service information for accomplishment of
the eddy current inspection required by paragraphs (g) and (h) of
this AD.
Reporting Requirement
(i) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes
and Model A300 C4-605R Variant F airplanes: At the applicable time
specified in paragraph (i)(1) or (i)(2) of this AD, submit a report
of findings (both positive and negative) of each inspection required
by this AD, in accordance with Airbus AOT A300-600-28A6075, dated
February 20, 2003. Information collection requirements contained in
this AD have been approved by the Office of Management and Budget
(OMB) under the provisions of the Paperwork Reduction Act of 1980
(44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number
2120-0056.
(1) For any inspection accomplished after May 19, 2004: Submit
the report within 10 days after performing that inspection.
(2) For any inspection accomplished before May 19, 2004: Submit
the report within 10 days after May 19, 2004.
Requirements of This AD
Repetitive Inspections for New Airplanes
(j) For Model A300 B4-2C, B4-103, and B4-203 airplanes; Model
A310-203, -204, -221, and -222 airplanes; and Model A310-304, -322,
-324, and -325 airplanes: At the applicable compliance time
specified in paragraphs (j)(1) and (j)(2) of this AD, do a detailed
inspection of the pump bodies for cracking, damage, and missing and
broken fasteners; and do a high frequency eddy current (HFEC)
inspection of the fuel pump canisters for a cracked flange web, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-28-0084, dated June 28, 2005 (for Model A300 B4-2C,
B4-103, and B4-203 airplanes); or Airbus Service Bulletin A310-28-
2159, dated June 28, 2005 (for Model A310-203, -204, -221, and -222
airplanes and Model A310-304, -322, -324, and -325 airplanes), as
applicable. If any crack or damage to the pump bodies is found or
any missing or broken fastener is found, before further flight,
replace the fuel pump with a new fuel pump in accordance with the
applicable service bulletin. Repeat the detailed inspection of the
pump bodies thereafter at intervals not to exceed 3,000 flight
cycles. If no cracked flange web is found, repeat the HFEC
inspection of the fuel pump canisters thereafter at intervals not to
exceed 3,000 flight cycles. Accomplishing the replacements specified
in paragraph (l) of this AD terminates the repetitive detailed and
HFEC inspections.
(1) For Model A300 B4-2C, B4-103, and B4-203 airplanes: Inspect
before the airplane has accumulated 19,600 total flight cycles, or
within 1,000 flight cycles after the effective date of this AD,
whichever is later.
(2) For Model A310-203, -204, -221, and -222 airplanes and Model
A310-304, -322, -324, and -325 airplanes: Inspect before the
airplane has accumulated 27,000 total flight cycles, or within 1,000
flight cycles after the effective date of this AD, whichever is
later.
[[Page 15084]]
Corrective Action for Cracked Flange Web
(k) For Model A300 B4-2C, B4-103, and B4-203; Model A310-203, -
204, -221, and -222 airplanes; and Model A310-304, -322, -324, and -
325 airplanes: If any flange web is found cracked during any HFEC
inspection required by paragraph (j) of this AD, before further
flight after the inspection, replace the fuel pump canister with a
new fuel pump canister in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-28-0084, dated June 28,
2005; or Airbus Service Bulletin A310-28-2159, dated June 28, 2005,
as applicable. Repeat the HFEC inspection at the applicable
compliance times specified in paragraph (k)(1) or (k)(2) of this AD,
until the replacements specified in paragraph (l) of this AD are
accomplished.
(1) For Model A300 B4-2C, B4-103, and B4-203 airplanes: Inspect
within 19,600 flight cycles after replacing the fuel pump canisters
and thereafter at intervals not to exceed 3,000 flight cycles.
(2) For Model A310-203, -204, -221, and -222 airplanes and Model
A310-304, -322, -324, and -325 airplanes: Inspect within 27,000
flight cycles after replacing the fuel pump canisters and thereafter
at intervals not to exceed 3,000 flight cycles.
Terminating Action: Replacement of Fuel Pump Canisters
(l) For all airplanes: Within 66 months after the effective date
of this AD, replace the fuel pump canisters with new reinforced fuel
pump canisters, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-28-0085, dated July 18, 2005 (for
Model A300 B4-2C, B4-103, and B4-203 airplanes); Airbus Service
Bulletin A300-28-6089, Revision 01, dated November 28, 2005 (for
Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes and Model
A300 C4-605R Variant F airplanes); or Airbus Service Bulletin A310-
28-2160, dated July 18, 2005 (for Model A310-203, -204, -221, and -
222 airplanes and Model A310-304, -322, -324, and -325 airplanes),
as applicable. Replacement of a fuel pump canister terminates the
repetitive inspections required by paragraphs (f), (g), (h), (j) and
(k), as applicable, for that fuel pump canister only.
Credit for Previous Service Bulletin
(m) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes
and Model A300 C4-605R Variant F airplanes: Actions done before the
effective date of this AD in accordance with Airbus Service Bulletin
A300-28-6089, dated July 18, 2005, are acceptable for compliance
with the requirements of paragraph (l) of this AD.
Alternative Methods of Compliance (AMOCs)
(n)(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.
Related Information
(o) French airworthiness directive F-2005-199, dated December 7,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on March 10, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-4407 Filed 3-24-06; 8:45 am]
BILLING CODE 4910-13-P
