Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes, 34224-34228 [E8-13566]
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Federal Register / Vol. 73, No. 117 / Tuesday, June 17, 2008 / Proposed Rules
(2) The grower must establish a buffer
area surrounding gardenia production
areas. The buffer area must extend 20
feet from the edge of the production
area. Within the buffer area, the growing
of gardenias and the following green
scale host plants is prohibited: Ixora,
ginger (Alpinia purpurata), plumeria,
coffee, rambutan, litchi, guava, citrus,
anthurium, avocado, banana, cocoa,
macadamia, celery, Pluchea indica,
mango, orchids, and annona.
(3) An inspector must visually inspect
the cut blooms of gardenias in each
consignment prior to interstate
movement from Hawaii to the mainland
United States. If the inspector does not
detect green scale in the consignment,
the inspector will certify the
consignment in accordance with
§ 318.13–3(b). If the inspector finds
green scale in a consignment, that
consignment will be ineligible for
interstate movement from Hawaii.
(Approved by the Office of Management
and Budget under control number 0579–
0197)
jlentini on PROD1PC65 with PROPOSALS
§ 318.13–24
Rico.
Sweetpotatoes from Puerto
Sweetpotatoes from Puerto Rico may
be moved interstate to Atlantic Coast
ports north of and including Baltimore,
MD, under limited permit if treated in
accordance with part 305 of this chapter
or if the following conditions are met:
(a) The sweetpotatoes must be
certified by an inspector of Puerto Rico
as having been grown under the
following conditions:
(1) Fields in which the sweetpotatoes
have been grown must have been given
a preplanting treatment with an APHISapproved soil insecticide.
(2) Before planting in such treated
fields, the sweetpotato draws and vine
cuttings must have been dipped in an
APHIS-approved insecticidal solution.
(3) During the growing season an
approved insecticide must have been
applied to the vines at prescribed
intervals.
(b) An inspector of Puerto Rico must
certify that the sweetpotatoes have been
washed.
(c) The sweetpotatoes must be graded
by inspectors of Puerto Rico in
accordance with Puerto Rican standards
which do not provide a tolerance for
insect infestation or evidence of insect
injury and found by such inspectors to
comply with such standards prior to
movement from Puerto Rico.
(d) The sweetpotatoes must be
inspected by an inspector and found to
be free of the sweetpotato scarabee
(Euscepes postfasciatus Fairm).
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§ 318.13–25
Sweetpotatoes from Hawaii.
(a) Sweetpotatoes may be moved
interstate from Hawaii in accordance
with this section only if the following
conditions are met: 5
(1) The sweetpotatoes must be treated
in accordance with the vapor heat
treatment schedule specified in
§ 305.24.
(2) The sweetpotatoes must be
sampled, cut, and inspected and found
to be free of the ginger weevil
(Elytrotreinus subtruncatus). Sampling,
cutting, and inspection must be
performed under conditions that will
prevent any pests that may emerge from
the sampled sweetpotatoes from
infesting any other sweetpotatoes
intended for interstate movement in
accordance with this section.
(3) The sweetpotatoes must be
inspected and found to be free of the
gray pineapple mealybug (Dysmicoccus
neobrevipes) and the Kona coffee-root
knot nematode (Meloidogyne
konaensis).
(4)(i) Sweetpotatoes that are treated in
Hawaii must be packaged in the
following manner:
(A) The cartons must have no
openings that will allow the entry of
fruit flies and must be sealed with seals
that will visually indicate if the cartons
have been opened. They may be
constructed of any material that
prevents the entry of fruit flies and
prevents oviposition by fruit flies into
the fruit in the carton.6
(B) The pallet-load of cartons must be
wrapped before it leaves the treatment
facility in one of the following ways:
(1) With polyethylene sheet wrap;
(2) With net wrapping; or
(3) With strapping so that each carton
on an outside row of the pallet load is
constrained by a metal or plastic strap.
(C) Packaging must be labeled with
treatment lot numbers, packing and
treatment facility identification and
location, and dates of packing and
treatment.
(ii) Cartons of untreated sweetpotatoes
that are moving to the mainland United
States for treatment must be shipped in
shipping containers sealed prior to
interstate movement with seals that will
visually indicate if the shipping
containers have been opened.
5 Sweetpotatoes may also be moved interstate
from Hawaii with irradiation in accordance with
§ 305.34 of this chapter or after fumigation with
methyl bromide according to treatment schedule T–
101–b–3–1, as provided for in § 305.6(a) of this
chapter.
6 If there is a question as to the adequacy of a
carton, send a request for approval of the carton,
together with a sample carton, to the Animal and
Plant Health Inspection Service, Plant Protection
and Quarantine, Center for Plant Health Science
and Technology, 1730 Varsity Drive, Suite 400,
Raleigh, NC 27606.
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(5)(i) Certification on basis of
treatment. Certification shall be issued
by an inspector for the movement of
sweetpotatoes from Hawaii that have
been treated in accordance with part
305 of this chapter and handled in
Hawaii in accordance with this section.
(ii) Limited permit. A limited permit
shall be issued by an inspector for the
interstate movement of untreated
sweetpotato from Hawaii for treatment
on the mainland United States in
accordance with this section.
(b) [Reserved]
(Approved by the Office of Management and
Budget under control number 0579–0281)
Subpart—Fruits and Vegetables From
Puerto Rico or Virgin Islands
[Removed]
5. Subpart—Fruits and Vegetables
From Puerto Rico or Virgin Islands,
consisting of §§ 318.58 through 318.58–
16, is removed.
Subpart—Guam [Removed]
6. Subpart—Guam, consisting of
§§ 318.82 through 318.82–3, is removed.
Done in Washington, DC, this 10th day of
June 2008.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. E8–13480 Filed 6–16–08; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0657; Directorate
Identifier 2007–NM–296–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300, A310, and A300–600 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, A310, and A300–
600 series airplanes. The existing AD
currently requires repetitive detailed
visual inspections to detect cracks in the
pylon thrust and sideload fitting of the
wing, and replacement of any cracked
pylon thrust and sideload fitting with a
new fitting. This proposed AD would
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Federal Register / Vol. 73, No. 117 / Tuesday, June 17, 2008 / Proposed Rules
reduce the threshold and repetitive
intervals for the detailed inspection for
certain airplanes and would reduce the
applicability of the existing AD. This
proposed AD results from issuance of
mandatory continuing airworthiness
information by a foreign civil
airworthiness authority. We are
proposing this AD to detect and correct
cracks in the pylon thrust and sideload
fitting of the wing, which could result
in reduced structural integrity of the
airplane.
DATES: We must receive comments on
this proposed AD by July 17, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0657; Directorate Identifier
2007–NM–296–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
34225
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On July 24, 1998, we issued AD 98–
16–11, amendment 39–10687 (63 FR
40816, July 31, 1998), for certain Airbus
Model A300, A310, and A300–600
series airplanes. That AD requires
repetitive detailed visual inspections to
detect cracks in the pylon thrust and
sideload fitting of the wing, and
replacement of any cracked pylon thrust
and sideload fitting with a new fitting.
That AD resulted from issuance of
mandatory continuing airworthiness
information by a foreign civil
airworthiness authority. We issued that
AD to detect and correct cracks in the
pylon thrust and sideload fitting of the
wing, which could result in reduced
structural integrity of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 98–16–11, Airbus
has issued the following service
bulletins:
TABLE.—NEW SERVICE BULLETINS
For model—
A300–57–0232, Revision 02, dated February 21, 2000 ............................................................................................
A300–57–6079, Revision 04, dated February 21, 2000 ............................................................................................
A310–57–2075, Revision 03, dated December 1, 2006 ...........................................................................................
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Airbus service bulletin—
A300 series airplanes.
A300–600 series airplanes.
A310 series airplanes.
The repetitive detailed inspections
and replacement procedures are
essentially identical to those specified
in previous issues of the service
bulletins. (AD 98–16–11 refers to Airbus
Service Bulletins A300–57–0232,
Revision 01 (for Model A300 series
airplanes); A310–57–2075, Revision 01
(for Model A310 series airplanes); and
A300–57–6079, Revision 02 (for Model
A300–600 series airplanes); all dated
January 12, 1998; as the appropriate
sources of service information for
accomplishing the required actions.)
Revision 03 of Airbus Service Bulletin
A310–57–2075 reduces the detailed
inspection thresholds and repeat
intervals for certain airplanes. In
addition, the effectivity listing of all
three service bulletins has been revised
to remove airplanes that have been
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scrapped. No more work is necessary for
airplanes on which previous issues of
the service bulletins were done.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. The European Aviation
Safety Agency (EASA), which is the
Technical Agent for the Member States
of the European Community, mandated
the service information and issued
EASA airworthiness directive 2007–
0243, dated September 4, 2007, to
ensure the continued airworthiness of
these airplanes in the European Union.
FAA’s Determination and Requirements
of the Proposed AD
These airplanes are manufactured in
France and are type certificated for
operation in the United States under the
provisions of section 21.29 of the
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Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. As described
in FAA Order 8100.14A, ‘‘Interim
Procedures for Working with the
European Community on Airworthiness
Certification and Continued
Airworthiness,’’ dated August 12, 2005,
the EASA has kept the FAA informed of
the situation described above. We have
examined the EASA’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 98–16–11 and would continue to
require, at reduced thresholds and
repetitive intervals for certain airplanes,
repetitive detailed visual inspections to
detect cracks in the pylon thrust and
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Federal Register / Vol. 73, No. 117 / Tuesday, June 17, 2008 / Proposed Rules
sideload fitting of the wing, and would
continue to require replacement of any
cracked pylon thrust and sideload
fitting with a new fitting. This proposed
AD would also require accomplishing
the actions specified in service
information described previously.
Differences Between Proposed Rule and
EASA AD
The proposed AD would differ from
the parallel EASA airworthiness
directive in that it would not allow for
adjustment in compliance time based on
airplane utilization. In developing an
appropriate compliance time for this
proposed AD, the FAA considered not
only the manufacturer’s
recommendation, but the degree of
urgency associated with addressing the
subject unsafe condition, and the
average utilization of the affected fleet.
In light of these factors, we find the
compliance times specified in
paragraphs (f)(1) and (f)(2) of this
proposed AD to be warranted, in that
they represent an appropriate interval of
time allowable for affected airplanes to
continue to operate without
compromising safety.
Change to Existing AD
This proposed AD would retain all
requirements of AD 98–16–11. Since AD
98–16–11 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
98–16–11
paragraph (a) ............
paragraph (b) ............
existing AD to ‘‘detailed inspection’’ in
this action.
Costs of Compliance
This proposed AD would affect about
164 Model A300, A310, and A300–600
series airplanes of U.S. registry.
The inspections that are required by
AD 98–16–11 and retained in this
proposed AD take about 3 work hours
per airplane, at an average labor rate of
$80 per work hour. Based on these
figures, the estimated cost of the
currently required actions is $39,360, or
$240 per airplane, per inspection cycle.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
Corresponding
requirement in this
proposed AD
paragraph (f).
paragraph (g).
In addition, we have revised the
applicability of this proposed AD to
refer to the latest revisions of the service
information described previously.
We also changed all references to a
‘‘detailed visual inspection’’ in the
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–10687 (63
FR 40816, July 31, 1998) and adding the
following new airworthiness directive
(AD):
Airbus: Docket No. FAA–2008–0657;
Directorate Identifier 2007–NM–296–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by July 17, 2008.
Affected ADs
(b) This AD supersedes AD 98–16–11.
Applicability
(c) This AD applies to Airbus airplanes
identified in Table 1 of this AD, certificated
in any category.
TABLE 1.—APPLICABILITY
As identified in Airbus service bulletin—
(1) A300 series airplanes ...................................
(2) A310 series airplanes ...................................
(3) A300–600 series airplanes ...........................
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Model—
A300–57–0232, Revision 02, dated February 21, 2000.
A310–57–2075, Revision 03, dated December 1, 2006.
A300–57–6079, Revision 04, dated February 21, 2000.
Unsafe Condition
(d) This AD results from issuance of
mandatory continuing airworthiness
information by a foreign civil airworthiness
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authority. We are issuing this AD to detect
and correct cracks in the pylon thrust and
sideload fitting of the wing, which could
result in reduced structural integrity of the
airplane.
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Compliance
(e) You are responsible for having the
actions required by this AD performed within
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Federal Register / Vol. 73, No. 117 / Tuesday, June 17, 2008 / Proposed Rules
the compliance times specified, unless the
actions have already been done.
Requirements of AD 98–16–11:
Repetitive Detailed Inspections at Reduced
Thresholds and Repeat Intervals for Certain
Airplanes
(f) At the applicable time specified in
paragraph (f)(1) or (f)(2) of this AD: Perform
a detailed inspection to detect cracks in the
pylon thrust and sideload fitting of the wing,
in accordance with Airbus Service Bulletin
A300–57–0232, Revision 01 (for Model A300
series airplanes); A310–57–2075, Revision 01
(for Model A310 series airplanes); or A300–
57–6079, Revision 02 (for Model A300–600
series airplanes); all dated January 12, 1998;
as applicable; except as provided by
paragraph (h) of this AD.
(1) For Model A300 and A300–600 series
airplanes: Inspect prior to the accumulation
of 2,800 total flight cycles, or within 18
months after September 4, 1998 (the effective
date AD 98–16–11), whichever occurs later,
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and thereafter at intervals not to exceed 2,800
flight cycles.
(2) For Model A310 series airplanes:
Inspect at the earlier of the times specified
in paragraph (f)(2)(i) and (f)(2)(ii) of this AD.
Repeat thereafter at the applicable intervals
specified in Table 3 of this AD.
(i) Prior to the accumulation of 2,800 total
flight cycles, or within 18 months after
September 4, 1998, whichever occurs later.
(ii) At the applicable time specified in
Table 2 of this AD.
TABLE 2.—REDUCED INSPECTION THRESHOLDS FOR MODEL A310 SERIES AIRPLANES
Compliance time (whichever occurs later)
Model
Threshold
A310–200 series airplanes ..
A310–300 series airplanes
(short range).
A310–300 series airplanes
(long range).
Grace period
Before the accumulation of 1,500 total flight cycles or
3,000 total flight hours since first flight, whichever occurs first.
Before the accumulation of 1,300 total flight cycles or
3,800 total flight hours since first flight, whichever occurs first.
Before the accumulation of 800 total flight cycles or
4,000 total flight hours since first flight, whichever occurs first.
Within 800 flight cycles or 1,600 flight hours after the
effective date of this AD, whichever occurs first.
Within 800 flight cycles or 1,600 flight hours after the
effective date of this AD, whichever occurs first.
Within 800 flight cycles or 1,600 flight hours after the
effective date of this AD, whichever occurs first.
TABLE 3.—REDUCED REPEAT INTERVALS FOR MODEL A310 SERIES AIRPLANES
For Model—
Repeat the detailed inspection at the later of—
And, thereafter at intervals not to
exceed—
A310–200 series airplanes .............
Within 1,500 flight cycles or 3,000 flight hours since the last detailed
inspection, whichever occurs first; or within 800 flight cycles or
1,600 flight hours after the effective date of this AD, whichever occurs first.
Within 1,300 flight cycles or 3,800 flight hours since the last detailed
inspection, whichever occurs first; or within 800 flight cycles or
1,600 flight hours after the effective date of this AD, whichever occurs first.
Within 800 flight cycles or 4,000 flight hours since the last detailed inspection, whichever occurs first; or within 800 flight cycles or 1,600
flight hours after the effective date of this AD, whichever occurs
first.
1,500 flight cycles or 3,000 flight
hours, whichever occurs first.
A310–300 series airplanes (short
range).
A310–300 series airplanes (long
range).
Corrective Action
(g) If any crack is detected during any
inspection required by paragraph (f) of this
AD, prior to further flight, replace the pylon
thrust and sideload fitting with a new fitting
in accordance with Airbus Service Bulletin
A300–57–0232, Revision 01 (for Model A300
series airplanes); A310–57–2075, Revision 01
(for Model A310 series airplanes); or A300–
57–6079, Revision 02 (for Model A300–600
series airplanes); all dated January 12, 1998;
as applicable; except as provided by
paragraph (h) of this AD.
New Actions Required by This AD:
New Service Information
(h) For all airplanes: As of the effective
date of this AD, use only the
1,300 flight cycles or 3,800 flight
hours, whichever occurs first.
800 flight cycles or 4,000 flight
hours, whichever occurs first.
Accomplishment Instructions of the
applicable service bulletin specified in Table
4 of this AD to do the repetitive detailed
inspections required by paragraph (f) of this
AD and the replacement required by
paragraph (g) of this AD.
TABLE 4.—NEW SERVICE BULLETINS
For model—
(1) A300–57–0232, Revision 02, dated February 21, 2000 ..................................................................................
(2) A300–57–6079, Revision 04, dated February 21, 2000 ..................................................................................
(3) A310–57–2075, Revision 03, dated December 1, 2006 .................................................................................
jlentini on PROD1PC65 with PROPOSALS
Airbus service bulletin—
A300 series airplanes.
A300–600 series airplanes.
A310 series airplanes.
(i) Actions done before the effective date of
this AD in accordance with Airbus Service
Bulletins A300–57–6079, Revision 02, dated
January 12, 1998, or Revision 03, dated
October 25, 1999 (for Model A300–600 series
airplanes); A310–57–2075, Revision 01,
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dated January 12, 1998, or Revision 02, dated
February 21, 2000 (for Model A310 series
airplanes); or A300–57–0232, Revision 01,
dated January 12, 1998 (for Model A300
series airplanes); are acceptable for
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compliance with the corresponding
requirements of this AD.
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Federal Register / Vol. 73, No. 117 / Tuesday, June 17, 2008 / Proposed Rules
Alternative Methods of Compliance
(AMOCs)
(j) The Manager, International Branch,
ANM–116, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send
information to ATTN: Vladimir Ulyanov,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1138; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
Related Information
(k) European Aviation Safety Agency
(EASA) airworthiness directive 2007–0243,
dated September 4, 2007, also addresses the
subject of this AD.
Issued in Renton, Washington, on June 10,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–13566 Filed 6–16–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27739; Directorate
Identifier 2006–NM–250–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330 Airplanes; and Model A340–200
and –300 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
jlentini on PROD1PC65 with PROPOSALS
SUMMARY: We are revising an original
NPRM for the products listed above.
This action revises the original NPRM
by expanding the scope. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
*
*
*
*
*
The aim of * * * [Special Federal Aviation
Regulation (SFAR) 88] is to require all
holders of type certificates * * * to carry out
a definition review against explosion
hazards.
The unsafe condition is the potential of
ignition sources inside fuel tanks,
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which, in combination with flammable
fuel vapors, could result in fuel tank
explosions and consequent loss of the
airplane. The proposed AD would
require actions that are intended to
address the unsafe condition described
in the MCAI.
DATES: We must receive comments on
this proposed AD by July 14, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington
98057–3356; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–27739; Directorate Identifier
2006–NM–250–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
PO 00000
Frm 00027
Fmt 4702
Sfmt 4702
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We proposed to amend 14 CFR part
39 with an earlier NPRM for the
specified products, which was
published in the Federal Register on
March 30, 2007 (72 FR 15063). That
earlier NPRM proposed to require
actions intended to address the unsafe
condition for the products listed above.
Since that NPRM was issued, we have
determined that additional bonding
points must be modified and that the
compliance time for performing the
action specified in paragraph (f)(4)(ii) of
this supplemental NPRM (increasing the
distance between metallic parts on the
trimmable horizontal stabilizer (THS)
trim tank) may be extended for airplanes
that are already compliant with certain
requirements of Airbus All Operators
Telex (AOT) 55–03, dated August 22,
1996. In addition, we have referred to
the latest revisions of the service
bulletins as the appropriate sources of
service information for accomplishing
certain actions in this supplemental
NPRM. European Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Community, has issued
Airworthiness Directive 2007–0278,
dated November 5, 2007 [Corrected:
November 8, 2007] (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
You may obtain further information by
examining the MCAI in the AD docket.
The MCAI states:
[T]he FAA published SFAR 88 (Special
Federal Aviation Regulation 88).
By mail referenced 04/00/02/07/01–L296
of March 4th, 2002 and 04/00/02/07/03–L024
of February 3rd, 2003 the JAA (Joint Aviation
Authorities) recommended to the National
Aviation Authorities (NAA) the application
of a similar regulation.
The aim of this regulation is to require all
holders of type certificates for passenger
transport aircraft certified after January 1st,
1958 with a capacity of 30 passengers or
more, or a payload of 3,402 kg or more, to
carry out a definition review against
explosion hazards.
Consequently, the following measures [are]
rendered mandatory * * *:
• [Inspection and] replacement [if
necessary] of the white P-clips by blue Pclips which are more fuel resistant remove
the risks of fuel quantity indicator (FQI) and
fuel level sensor system (FLSS) harnesses
chafing against the metallic part of the P-clip,
• Modification of electrical bonding of
equipment installed in fuel tanks in order to
re-establish the conformity with the design
definition by introducing additional bonding
E:\FR\FM\17JNP1.SGM
17JNP1
]]>Agencies
[Federal Register Volume 73, Number 117 (Tuesday, June 17, 2008)]
[Proposed Rules]
[Pages 34224-34228]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-13566]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0657; Directorate Identifier 2007-NM-296-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A310, and A300-600
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, A310, and
A300-600 series airplanes. The existing AD currently requires
repetitive detailed visual inspections to detect cracks in the pylon
thrust and sideload fitting of the wing, and replacement of any cracked
pylon thrust and sideload fitting with a new fitting. This proposed AD
would
[[Page 34225]]
reduce the threshold and repetitive intervals for the detailed
inspection for certain airplanes and would reduce the applicability of
the existing AD. This proposed AD results from issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. We are proposing this AD to detect and correct cracks in the
pylon thrust and sideload fitting of the wing, which could result in
reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by July 17, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0657;
Directorate Identifier 2007-NM-296-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On July 24, 1998, we issued AD 98-16-11, amendment 39-10687 (63 FR
40816, July 31, 1998), for certain Airbus Model A300, A310, and A300-
600 series airplanes. That AD requires repetitive detailed visual
inspections to detect cracks in the pylon thrust and sideload fitting
of the wing, and replacement of any cracked pylon thrust and sideload
fitting with a new fitting. That AD resulted from issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. We issued that AD to detect and correct cracks in the pylon
thrust and sideload fitting of the wing, which could result in reduced
structural integrity of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 98-16-11, Airbus has issued the following
service bulletins:
Table.--New Service Bulletins
------------------------------------------------------------------------
Airbus service bulletin-- For model--
------------------------------------------------------------------------
A300-57-0232, Revision 02, A300 series airplanes.
dated February 21, 2000.
A300-57-6079, Revision 04, A300-600 series airplanes.
dated February 21, 2000.
A310-57-2075, Revision 03, A310 series airplanes.
dated December 1, 2006.
------------------------------------------------------------------------
The repetitive detailed inspections and replacement procedures are
essentially identical to those specified in previous issues of the
service bulletins. (AD 98-16-11 refers to Airbus Service Bulletins
A300-57-0232, Revision 01 (for Model A300 series airplanes); A310-57-
2075, Revision 01 (for Model A310 series airplanes); and A300-57-6079,
Revision 02 (for Model A300-600 series airplanes); all dated January
12, 1998; as the appropriate sources of service information for
accomplishing the required actions.) Revision 03 of Airbus Service
Bulletin A310-57-2075 reduces the detailed inspection thresholds and
repeat intervals for certain airplanes. In addition, the effectivity
listing of all three service bulletins has been revised to remove
airplanes that have been scrapped. No more work is necessary for
airplanes on which previous issues of the service bulletins were done.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The European
Aviation Safety Agency (EASA), which is the Technical Agent for the
Member States of the European Community, mandated the service
information and issued EASA airworthiness directive 2007-0243, dated
September 4, 2007, to ensure the continued airworthiness of these
airplanes in the European Union.
FAA's Determination and Requirements of the Proposed AD
These airplanes 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. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, the EASA has kept the FAA informed of the
situation described above. We have examined the EASA'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 98-16-11 and would continue to
require, at reduced thresholds and repetitive intervals for certain
airplanes, repetitive detailed visual inspections to detect cracks in
the pylon thrust and
[[Page 34226]]
sideload fitting of the wing, and would continue to require replacement
of any cracked pylon thrust and sideload fitting with a new fitting.
This proposed AD would also require accomplishing the actions specified
in service information described previously.
Differences Between Proposed Rule and EASA AD
The proposed AD would differ from the parallel EASA airworthiness
directive in that it would not allow for adjustment in compliance time
based on airplane utilization. In developing an appropriate compliance
time for this proposed AD, the FAA considered not only the
manufacturer's recommendation, but the degree of urgency associated
with addressing the subject unsafe condition, and the average
utilization of the affected fleet. In light of these factors, we find
the compliance times specified in paragraphs (f)(1) and (f)(2) of this
proposed AD to be warranted, in that they represent an appropriate
interval of time allowable for affected airplanes to continue to
operate without compromising safety.
Change to Existing AD
This proposed AD would retain all requirements of AD 98-16-11.
Since AD 98-16-11 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
------------------------------------------------------------------------
Corresponding requirement
Requirement in AD 98-16-11 in this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
------------------------------------------------------------------------
In addition, we have revised the applicability of this proposed AD
to refer to the latest revisions of the service information described
previously.
We also changed all references to a ``detailed visual inspection''
in the existing AD to ``detailed inspection'' in this action.
Costs of Compliance
This proposed AD would affect about 164 Model A300, A310, and A300-
600 series airplanes of U.S. registry.
The inspections that are required by AD 98-16-11 and retained in
this proposed AD take about 3 work hours per airplane, at an average
labor rate of $80 per work hour. Based on these figures, the estimated
cost of the currently required actions is $39,360, or $240 per
airplane, per inspection cycle.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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 39-10687 (63 FR 40816, July 31, 1998) and adding the
following new airworthiness directive (AD):
Airbus: Docket No. FAA-2008-0657; Directorate Identifier 2007-NM-
296-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by July 17,
2008.
Affected ADs
(b) This AD supersedes AD 98-16-11.
Applicability
(c) This AD applies to Airbus airplanes identified in Table 1 of
this AD, certificated in any category.
Table 1.--Applicability
------------------------------------------------------------------------
As identified in Airbus service
Model-- bulletin--
------------------------------------------------------------------------
(1) A300 series airplanes............ A300-57-0232, Revision 02, dated
February 21, 2000.
(2) A310 series airplanes............ A310-57-2075, Revision 03, dated
December 1, 2006.
(3) A300-600 series airplanes........ A300-57-6079, Revision 04, dated
February 21, 2000.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from issuance of mandatory continuing
airworthiness information by a foreign civil airworthiness
authority. We are issuing this AD to detect and correct cracks in
the pylon thrust and sideload fitting of the wing, which could
result in reduced structural integrity of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within
[[Page 34227]]
the compliance times specified, unless the actions have already been
done.
Requirements of AD 98-16-11:
Repetitive Detailed Inspections at Reduced Thresholds and Repeat
Intervals for Certain Airplanes
(f) At the applicable time specified in paragraph (f)(1) or
(f)(2) of this AD: Perform a detailed inspection to detect cracks in
the pylon thrust and sideload fitting of the wing, in accordance
with Airbus Service Bulletin A300-57-0232, Revision 01 (for Model
A300 series airplanes); A310-57-2075, Revision 01 (for Model A310
series airplanes); or A300-57-6079, Revision 02 (for Model A300-600
series airplanes); all dated January 12, 1998; as applicable; except
as provided by paragraph (h) of this AD.
(1) For Model A300 and A300-600 series airplanes: Inspect prior
to the accumulation of 2,800 total flight cycles, or within 18
months after September 4, 1998 (the effective date AD 98-16-11),
whichever occurs later, and thereafter at intervals not to exceed
2,800 flight cycles.
(2) For Model A310 series airplanes: Inspect at the earlier of
the times specified in paragraph (f)(2)(i) and (f)(2)(ii) of this
AD. Repeat thereafter at the applicable intervals specified in Table
3 of this AD.
(i) Prior to the accumulation of 2,800 total flight cycles, or
within 18 months after September 4, 1998, whichever occurs later.
(ii) At the applicable time specified in Table 2 of this AD.
Table 2.--Reduced Inspection Thresholds for Model A310 Series Airplanes
------------------------------------------------------------------------
Compliance time (whichever occurs later)
Model -------------------------------------------
Threshold Grace period
------------------------------------------------------------------------
A310-200 series airplanes... Before the Within 800 flight
accumulation of cycles or 1,600
1,500 total flight flight hours after
cycles or 3,000 the effective date
total flight hours of this AD,
since first flight, whichever occurs
whichever occurs first.
first.
A310-300 series airplanes Before the Within 800 flight
(short range). accumulation of cycles or 1,600
1,300 total flight flight hours after
cycles or 3,800 the effective date
total flight hours of this AD,
since first flight, whichever occurs
whichever occurs first.
first.
A310-300 series airplanes Before the Within 800 flight
(long range). accumulation of 800 cycles or 1,600
total flight cycles flight hours after
or 4,000 total the effective date
flight hours since of this AD,
first flight, whichever occurs
whichever occurs first.
first.
------------------------------------------------------------------------
Table 3.--Reduced Repeat Intervals for Model A310 Series Airplanes
------------------------------------------------------------------------
Repeat the detailed And, thereafter
For Model-- inspection at the at intervals not
later of-- to exceed--
------------------------------------------------------------------------
A310-200 series airplanes..... Within 1,500 flight 1,500 flight
cycles or 3,000 cycles or 3,000
flight hours since flight hours,
the last detailed whichever
inspection, whichever occurs first.
occurs first; or
within 800 flight
cycles or 1,600
flight hours after
the effective date of
this AD, whichever
occurs first.
A310-300 series airplanes Within 1,300 flight 1,300 flight
(short range). cycles or 3,800 cycles or 3,800
flight hours since flight hours,
the last detailed whichever
inspection, whichever occurs first.
occurs first; or
within 800 flight
cycles or 1,600
flight hours after
the effective date of
this AD, whichever
occurs first.
A310-300 series airplanes Within 800 flight 800 flight
(long range). cycles or 4,000 cycles or 4,000
flight hours since flight hours,
the last detailed whichever
inspection, whichever occurs first.
occurs first; or
within 800 flight
cycles or 1,600
flight hours after
the effective date of
this AD, whichever
occurs first.
------------------------------------------------------------------------
Corrective Action
(g) If any crack is detected during any inspection required by
paragraph (f) of this AD, prior to further flight, replace the pylon
thrust and sideload fitting with a new fitting in accordance with
Airbus Service Bulletin A300-57-0232, Revision 01 (for Model A300
series airplanes); A310-57-2075, Revision 01 (for Model A310 series
airplanes); or A300-57-6079, Revision 02 (for Model A300-600 series
airplanes); all dated January 12, 1998; as applicable; except as
provided by paragraph (h) of this AD.
New Actions Required by This AD:
New Service Information
(h) For all airplanes: As of the effective date of this AD, use
only the Accomplishment Instructions of the applicable service
bulletin specified in Table 4 of this AD to do the repetitive
detailed inspections required by paragraph (f) of this AD and the
replacement required by paragraph (g) of this AD.
Table 4.--New Service Bulletins
------------------------------------------------------------------------
Airbus service bulletin-- For model--
------------------------------------------------------------------------
(1) A300-57-0232, Revision A300 series airplanes.
02, dated February 21, 2000.
(2) A300-57-6079, Revision A300-600 series airplanes.
04, dated February 21, 2000.
(3) A310-57-2075, Revision A310 series airplanes.
03, dated December 1, 2006.
------------------------------------------------------------------------
(i) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletins A300-57-6079, Revision 02,
dated January 12, 1998, or Revision 03, dated October 25, 1999 (for
Model A300-600 series airplanes); A310-57-2075, Revision 01, dated
January 12, 1998, or Revision 02, dated February 21, 2000 (for Model
A310 series airplanes); or A300-57-0232, Revision 01, dated January
12, 1998 (for Model A300 series airplanes); are acceptable for
compliance with the corresponding requirements of this AD.
[[Page 34228]]
Alternative Methods of Compliance (AMOCs)
(j) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(k) European Aviation Safety Agency (EASA) airworthiness
directive 2007-0243, dated September 4, 2007, also addresses the
subject of this AD.
Issued in Renton, Washington, on June 10, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-13566 Filed 6-16-08; 8:45 am]
BILLING CODE 4910-13-P
