Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes, 8604-8608 [E7-2512]
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8604
Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations
free of evidence of Phytophthora
ramorum infestation at the time of
inspection. Certification is valid for 1
year and must be renewed each year to
continue shipping plants interstate.
(e) Additions to the lists of proven
hosts and associated plants. In the event
that APHIS informs a nursery owner
that additional proven hosts or
associated plants exist, but those taxa
are not yet listed in this subpart, the
following provisions apply:
(1) Nurseries operating under a
compliance agreement in accordance
with § 301.92–6 may continue to ship
plants interstate in accordance with this
subpart.
(2) Nurseries that had not previously
contained any regulated or associated
articles, and that had been inspected in
accordance with § 301.92–11(b)(3) and
allowed to ship plants interstate without
certificate, but that contain a newly
identified proven host or associated
plant must cease interstate shipments of
regulated articles and associated hosts
until the nursery is reinspected and
found free of evidence of Phytophthora
ramorum in accordance with § 301.92–
11. Nurseries that come under
regulation during winter dormancy
periods and that are not able to be
inspected in accordance with § 301.92–
11 prior to desired shipments of nonhost nursery stock may be allowed to
ship non-host nursery stock interstate at
the discretion of an inspector.
(Approved by the Office of Management and
Budget under control number 0579–0310)
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§ 301.92–12
Testing protocols.
Samples must be analyzed using a
methodology approved by APHIS at a
laboratory approved by APHIS. The
following methodology is approved by
APHIS.
(a) Optional ELISA Prescreening. An
APHIS-approved ELISA may be used to
prescreen plant samples to determine
the presence of Phytophthora spp.
(1) Negative prescreening results. If all
samples from a single nursery are found
to be negative through APHIS-approved
ELISA prescreening, no further testing is
required. The nursery may be
considered free of evidence of
Phytophthora ramorum, and plants in
the nursery are eligible for interstate
movement under certificate in
accordance with § 301.92–5.
(2) Positive prescreening results. If
ELISA prescreening reveals the presence
of Phytophthora spp. in any plants, each
sample that returns positive ELISA
results must be tested as provided in
paragraph (b) of this section.
(b) Mandatory testing procedures. If
ELISA prescreening is not performed, or
if results of ELISA prescreening are
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positive for Phytophthora spp. in any
sample, the sample must be analyzed
using an APHIS-approved test. Samples
will be considered positive for
Phytophthora ramorum based on
positive results of any approved test.
Positive PCR or other molecular tests do
not require confirmatory culture tests,
nor do positive culture tests require
confirmatory PCR or other molecular
tests; however, if culture tests return
other than positive results, an APHISapproved PCR or other molecular test
must be conducted, as provided in
paragraph (b)(1) of this section.
(1) PCR or other molecular tests.
(i) Negative results. If the results of
PCR or other molecular tests are
negative for all samples in a nursery, no
further testing is required. The nursery
may be considered free of evidence of
Phytophthora ramorum and plants in
the nursery are eligible for interstate
movement under certificate in
accordance with § 301.92–5.
(ii) Positive results. If any samples
tested using PCR or other molecular
tests return positive results for
Phytophthora ramorum, the nursery
from which they originate is prohibited
from moving plants interstate. The
nursery will be eligible to ship certain
plants interstate when an inspector
determines that those plants are free of
evidence of Phytophthora ramorum.
(2) Culture Test.
(i) Negative results. If the results of
culture tests are other than positive for
any samples taken from a single
nursery, plants in the nursery must
continue to be withheld from shipment
in accordance with § 301.92–11 and
each plant sample must be tested again
using a PCR or other molecular test, as
described in this section.
(ii) Positive results. If any culture tests
return positive results for Phytophthora
ramorum, the nursery from which they
originate is prohibited from moving
plants interstate as directed by an
inspector. The nursery will be eligible to
ship certain plants interstate when an
inspector determines that those plants
are free of evidence of Phytophthora
ramorum.
(c) Other test methods. Other test
methods may be acceptable if approved
by APHIS.
Done in Washington, DC, this 16th day of
February 2007.
Bruce Knight,
Under Secretary for Marketing and Regulatory
Programs.
[FR Doc. 07–892 Filed 2–26–07; 8:45 am]
BILLING CODE 3410–34–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25890; Directorate
Identifier 2006–NM–115–AD; Amendment
39–14943; AD 2007–04–11]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B2 and B4 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to all Airbus Model A300
B2, B4–100, and B4–200 series
airplanes. That AD currently requires
supplemental structural inspections to
detect fatigue cracking, and repair of
cracked structure. This new AD requires
revising the maintenance program by
incorporating new and revised
supplemental structural inspections,
inspection intervals, and repairs; and
repair of any damaged, cracked, or
corroded structure; which would end
the existing supplement structural
inspections. This AD results from a
review of service history and reports
received from the current supplemental
structural inspection document
program. We are issuing this AD to
prevent reduced structural integrity of
these airplanes due to fatigue cracking.
DATES: This AD becomes effective April
3, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of April 3, 2007.
On August 9, 1996 (61 FR 35122, July
5, 1996), the Director of the Federal
Register approved the incorporation by
reference of Airbus Industrie
Supplemental Structural Inspection
Document, dated September 1989; and
Airbus Industrie A300 Supplemental
Structural Inspection Document,
Revision 2, dated June 1994.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
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International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1622; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket 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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 96–13–11, amendment
39–9679 (61 FR 35122, July 5, 1996).
The existing AD applies to all Airbus
Model A300 B2, B4–100, and B4–200
series airplanes. That NPRM was
published in the Federal Register on
September 26, 2006 (71 FR 56058). That
NPRM proposed to continue to require
supplemental structural inspections to
detect fatigue cracking, and repair of
cracked structure. That NPRM also
proposed to require revising the
maintenance program by incorporating
new and revised supplemental
structural inspections, inspection
intervals, and repairs; and repair of any
damaged, cracked, or corroded
structure; which would end the existing
supplement structural inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received.
Request for Change to the Applicability
Airbus, the manufacturer, requests
that we exclude the A300–600 series
airplanes from the AD applicability. The
commenter refers us to page 1–A of
Airbus A300 Airworthiness Limitation
8605
Items Document SEM2/95A.1090/05,
Issue 3, dated September 2005, as
revised by Airbus Temporary Revision
3.1, dated April 2006, which does not
include A300–600 series airplanes.
We agree with the commenter’s
request. We do not want any reader of
this AD to infer that A300–600 series
airplanes are included, and have
changed the applicability to exclude
those airplanes in paragraph (c) of this
AD.
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD with the change described
previously. We have determined that
this change will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Work
hours
Action
Implementation of supplemental structural inspection program (required by AD 96–13–11).
Revision of the FAA-approved maintenance program (new action).
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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
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 AD will
not have federalism implications under
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Average labor
rate per hour
Parts
Number of
U.S.-registered
airplanes
Fleet cost
597
$80
None ....
$47,760
29
$1,385,040
10
80
None ....
800
29
23,200
Executive Order 13132. This AD will
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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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 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, Incorporation by reference,
Safety.
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Cost per airplane
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Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–9679 (61
FR 35122, July 5, 1996) and by adding
the following new airworthiness
directive (AD):
I
2007–04–11 Airbus: Amendment 39–14943.
Docket No. FAA–2006–25890;
Directorate Identifier 2006–NM–115–AD.
Effective Date
(a) This AD becomes effective April 3,
2007.
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Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations
Affected ADs
(b) This AD supersedes AD 96–13–11.
Applicability
(c) This AD applies to all Airbus Model
A300 B2 and B4 series airplanes, certificated
in any category, excluding A300–600 series
airplanes.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance according
to paragraph (x) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued damage tolerance of the affected
structure. The FAA has provided guidance
for this determination in Advisory Circular
(AC) 25–1529.
Unsafe Condition
(d) This AD results from a review of service
history and reports received from the current
supplemental structural inspection document
program. We are issuing this AD to prevent
reduced structural integrity of these airplanes
due to fatigue cracking.
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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.
Requirements of AD 96–13–11
(f) Within one year after March 9, 1993 (the
effective date of AD 93–01–24, amendment
39–8478), incorporate a revision into the
FAA-approved maintenance inspection
program that provides for supplemental
maintenance inspections, modifications,
repair, or replacement of the significant
structural details (SSD) and significant
structural items (SSI) specified in ‘‘Airbus
Industrie A300 Supplemental Structural
Inspection Document’’ (SSID), dated
September 1989 (hereafter referred to as ‘‘the
SSID’’).
(g) Within one year after August 9, 1996
(the effective date of AD 96–13–11), replace
the revision of the FAA-approved
maintenance program required by paragraph
(f) of this AD with the inspections, inspection
intervals, repairs, and replacements defined
in ‘‘Airbus Industrie A300 Supplemental
Structural Inspection Document’’ (SSID),
Revision 2, dated June 1994 (hereafter
referred to as ‘‘Revision 2 of the SSID’’).
Accomplish the actions specified in the
service bulletins identified in Section 6, ‘‘SB
Reference List,’’ Revision 2 of the SSID, at the
times specified in those service bulletins.
The actions are to be accomplished in
accordance with those service bulletins.
(1) For airplanes that have exceeded the
threshold specified in any of the service
bulletins identified in Section 6, ‘‘SB
Reference List,’’ Revision 2 of the SSID:
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Accomplish the actions specified in those
service bulletins within the grace period
specified in that service bulletin. The grace
period is to be measured from August 9,
1996.
(2) For airplanes that have exceeded the
threshold specified in any of the service
bulletins identified in Section 6, ‘‘SB
Reference List,’’ Revision 2 of the SSID, and
a grace period is not specified in that service
bulletin: Accomplish the actions specified in
that service bulletin within 1,500 flight
cycles after August 9, 1996.
(h) If any cracked structure is detected
during the inspections required by either
paragraph (f) or (g) of this AD, prior to further
flight, permanently repair the cracked
structure in accordance with either paragraph
(h)(1), (h)(2), or (h)(3) of this AD.
Note 2: A permanent repair is defined as
a repair that meets the certification basis of
the airplane, and does not require additional
modification at a later date.
(1) The service bulletins listed in Section
6, ‘‘SB Reference List,’’ of the SSID (for
airplanes that are currently being inspected
in accordance with paragraph (f) of this AD);
or in accordance with a method approved by
the Manager, International Branch, ANM–116
(formerly the Standardization Branch, ANM–
113), FAA, Transport Airplane Directorate, if
a permanent repair is not specified in any of
these service bulletins. Or
(2) The service bulletins listed in Section
6, ‘‘SB Reference List,’’ of Revision 2 of the
SSID (for airplanes that are currently being
inspected in accordance with paragraph (g) of
this AD); or in accordance with a method
approved by the Manager, International
Branch, ANM–116 (formerly the
Standardization Branch, ANM–113), if a
permanent repair is not specified in any of
these service bulletins. Or,
(3) Other permanent repair data meeting
the certification basis of the airplane which
is approved by the Manager, International
Branch, ANM–116 (formerly the
Standardization Branch, ANM–113); or by
´ ´
the Direction Generale de l’Aviation Civile
(DGAC) of France.
(i) For airplanes identified as Fleet Leader
Program (FLP) in Section 5, ‘‘Fleet Leader
Program,’’ of the SSID or Revision 2 of the
SSID: Inspect according to the instructions
and intervals specified in paragraph 4.4,
‘‘Adjustment of Inspection Requirements and
DSG,’’ of Section 4, or Section 9, as
applicable, of the SSID (for airplanes
inspected in accordance with paragraph (f) of
this AD), or Revision 2 of the SSID (for
airplanes inspected in accordance with
paragraph (g) of this AD), for each SSD.
(j) For the purpose of accomplishing
paragraphs (i), (k), (l), and (n) of this AD,
operators shall not use paragraph 6.2,
‘‘Complete RR Method,’’ of Section 9 of the
SSID to calculate inspection thresholds and
intervals.
(k) For Model A300–B2 and B2K–3C series
airplanes: For any SSD that has exceeded the
values of the threshold specified in
paragraph 6, ‘‘Inspection Threshold and
Intervals,’’ Section 9 of the SSID, inspect at
the time specified in either paragraph (k)(1)
or (k)(2) of this AD, as applicable.
(1) For airplanes inspected in accordance
with paragraph (f) of this AD: Inspect within
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2,000 landings after March 9, 1993, in
accordance with the SSID. Or,
(2) For airplanes inspected in accordance
with paragraph (g) of this AD: Inspect within
2,000 landings after August 9, 1996, in
accordance with Revision 2 of the SSID.
(l) For Model A300–B4 series airplanes:
For any SSD that has exceeded the values of
the threshold specified in paragraph 6,
‘‘Inspection Threshold and Intervals,’’
Section 9 of the SSID, inspect at the time
specified in either paragraph (l)(1) or (l)(2) of
this AD, as applicable.
(1) For airplanes inspected in accordance
with paragraph (f) of this AD: Inspect within
1,500 landings after March 9, 1993 [the
effective date of AD 93–01–24, amendment
39–8478]. Or,
(2) For airplanes inspected in accordance
with paragraph (g) of this AD: Inspect within
1,500 landings after August 9, 1996.
(m) For airplanes identified as FLP in
Section 5, ‘‘Fleet Leader Program,’’ of the
SSID or Revision 2 of the SSID: Within one
year after August 9, 1996, apply the basic
requirements given in Revision 2 of the SSID.
(n) For airplanes that are subject to the
requirements of paragraph (g) of this AD, and
have exceeded the initial inspection
threshold specified in paragraph 4.4,
‘‘Adjustment of Inspection Requirements and
DSG,’’ of Section 4, or paragraph 6,
‘‘Inspection Threshold and Intervals,’’ of
Section 9, for each SSD: Perform the initial
inspection prior to the accumulation of the
number of flight cycles specified in
paragraph 7, ‘‘Additional Information,’’
Section 9, of Revision 2 of the SSID.
Note 3: Fatigue ratings are not applicable
to these allowances; therefore, no adjustment
is required.
Note 4: Paragraph (n) of this AD provides
the ‘‘grace’’ periods for those airplanes that
are new to the FLP or that have newly added
or revised SSID requirements in accordance
with paragraph (g) of this AD.
(o) The grace period provided by paragraph
(n) of this AD is also applicable to the
thresholds and/or repeat intervals for each
SSD for which the inspection interval or
threshold was reduced in accordance with
the requirements of paragraph (g) of this AD.
(p) For FLP airplanes identified in Section
5, ‘‘Fleet Leader Program,’’ of the SSID or
Revision 2 of the SSID that are listed in
Section 7, ‘‘SSI Limitation List,’’ of the SSID
(for airplanes that are currently being
inspected in accordance with paragraph (f) of
this AD), or Revision 2 of the SSID (for
airplanes that are currently being inspected
in accordance with paragraph (g) of this AD):
Inspect at intervals not to exceed the interval
specified for each SSI, in accordance with the
values given in Section 7, ‘‘SSI Limitation
List,’’ of the SSID or Revision 2 of the SSID,
as applicable.
(q) For all airplanes: All inspection results,
positive or negative, must be reported to
Airbus in accordance with either paragraph
(q)(1) or (q)(2) of this AD, as applicable.
Information collection requirements
contained in this regulation 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.
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3501 et seq.) and have been assigned OMB
Control Number 2120–0056.
(1) For FLP airplanes, identified in Section
5, ‘‘Fleet Leader Program,’’ of the SSID or
Revision 2 of the SSID: Submit reports in
accordance with the instructions in
paragraph 5.2, ‘‘SSIP Inspection Reporting,’’
of Section 5, and paragraph 7.1, ‘‘General,’’
of Section 7 of the SSID (for airplanes that
are currently being inspected in accordance
with paragraph (f) of this AD); or Revision 2
of the SSID (for airplanes inspected in
accordance with paragraph (g) of this AD).
(2) For all airplanes that are subject to
Section 6, ‘‘SB Reference List,’’ of the SSID:
Submit reports in accordance with the
instructions in the applicable service
bulletins identified in Section 6 of the SSID
(for airplanes that are currently being
inspected in accordance with paragraph (f) of
this AD); or Revision 2 of the SSID (for
airplanes that are currently being inspected
in accordance with paragraph (g) of this AD).
New Requirements of This AD
Revision of the FAA-Approved Maintenance
Inspection Program
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(r) Within 12 months after the effective
date of this AD, replace the revision of the
FAA-approved maintenance program
required by paragraph (g) of this AD with the
supplemental structural inspections,
inspection intervals, and repairs defined in
Airbus A300 Airworthiness Limitation Items
(ALI) Document SEM2/95A.1090/05, Issue 3,
dated September 2005, as revised by Airbus
Temporary Revision (TR) 3.1, dated April
2006 (hereafter referred to as ‘‘Issue 3 of the
ALI’’). Accomplish the actions specified in
Issue 3 of the ALI at the times specified in
that ALI, except as provided by paragraph (s)
of this AD. The actions must be
accomplished in accordance with Issue 3 of
the ALI. Accomplishing the applicable initial
ALI tasks constitutes terminating action for
the requirements of paragraphs (f) through (q)
of this AD.
(s) For airplanes that have exceeded the
threshold or intervals specified in Issue 3 of
the ALI for the application tolerance on the
first interval for new and revised
requirements and have exceeded 50 percent
of the intervals specified in sections D and
E of Issue 3 of the ALI: Do the actions within
6 months after the effective date of this AD.
Corrective Actions
(t) Damaged, cracked, or corroded structure
detected during any inspection done in
accordance with Issue 3 of the ALI must be
repaired, before further flight, in accordance
with Issue 3 of the ALI, except as provided
by paragraph (u) of this AD; or other data
meeting the certification basis of the airplane
which is approved by the Manager,
International Branch, ANM–116; or by the
European Aviation Safety Agency (EASA) (or
its delegated agent).
(u) Where Issue 3 of the ALI specifies
contacting Airbus for appropriate action:
Before further flight, repair the damaged,
cracked, or corroded structure using a
method approved by either the Manager,
International Branch, ANM–116; or the
EASA (or its delegated agent).
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14:03 Feb 26, 2007
Jkt 211001
No Fleet Sampling
(v) Although Issue 3 of the ALI specifies to
do a ‘‘Sampling Concept’’ in section B, this
AD prohibits the use of such a sampling
program and requires all affected airplanes of
the fleet to be inspected.
No Reporting
(w) Although Issue 3 of the ALI specifies
to submit certain information to the
manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance
(AMOCs)
(x)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) AMOCs approved previously in
accordance with AD 96–13–11 are approved
as AMOCs for the corresponding provisions
of paragraphs (f) through (q) of this AD.
Related Information
(y) EASA airworthiness directive 2006–
0071, dated March 30, 2006, also addresses
the subject of this AD.
Material Incorporated by Reference
(z) You must use Airbus A300
Airworthiness Limitation Items Document
SEM2/95A.1090/05, Issue 3, dated September
2005, as revised by Airbus A300
Airworthiness Limitation Items Document
SEM2/95A.1090/05, Temporary Revision 3.1,
including attachment, dated April 2006, and
including attachments dated September
2005; Airbus Industrie Supplemental
Structural Inspection Document, dated
September 1989; and Airbus Industrie A300
Supplemental Structural Inspection
Document, Revision 2, dated June 1994; as
applicable, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. Airbus A300 Airworthiness
Limitation Items Document SEM2/95A.1090/
05, Issue 3, dated September 2005, contains
the following effective pages:
Page number
1–SOC—10–
SOC.
1–TOC .........
Issue number
shown on
page
1–A ...............
Section SOC,
3.
Section TOC,
3.
Section A, 3
1–B—6–B .....
Section B, 3
1–C, 2 ..........
Section C, 3
1–D, 2–D, 3–
101.
1–E, 1–24 ....
Section D, 3
Section E, 3
1–F, 2–39 .....
Section F, 3
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Date shown
on page
September
2005.
September
2005.
September
2005.
September
2005.
September
2005.
September
2005.
September
2005.
September
2005.
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Page number
1–G, 20–G,
30–G, 101–
G.
2–G—19–G,
21–G—29–
G, 31–G—
100G, 102–
G—328–G.
1–App—3–
App.
Issue number
shown on
page
8607
Date shown
on page
Section G, 3
September
2005.
1 ...................
January
2004.
Section App,
3.
September
2005.
(Airbus A300 Airworthiness Limitation
Items Document SEM2/95A.1090/05, Issue 3,
dated September 2005, contains two page 1–
SOC and two page 190–G. The first page
identified as 1–SOC is the Record of Changes
and the second page 1–SOC is the first page
of the Summary of Changes. The first page
identified as page 190–G refers to
Airworthiness Limitation Item 546014, and
the second page 190–G refers to
Airworthiness Limitation Item 556001.)
Airbus A300 Airworthiness Limitations Items
Document SEM2/95A.1090/05, Temporary
Revision 3.1, dated April 2006, contains the
following effective pages:
Page number
1–T.R. 3.1–
4–T.R.3.1.
Section D, 3–
27.
Section E, 1–
4.
Section F, 2–
6.
Issue number
shown on
page
Date shown
on page
Original .........
April 2006.
T.R.3.1 .........
April 2006.
3 ...................
September
2005.
September
2005.
3 ...................
(1) The Director of the Federal Register
approved the incorporation by reference of
Airbus A300 Airworthiness Limitation Items
Document SEM2/95A.1090/05, Issue 3, dated
September 2005; as revised by Airbus A300
Airworthiness Limitation Items Document
SEM2/95A.1090/05, Temporary Revision 3.1,
including attachment, dated April 2006, and
including attachments, dated September
2005; in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
(2) On August 9, 1996 (61 FR 35122, July
5, 1996), the Director of the Federal Register
approved the incorporation by reference of
Airbus Industrie Supplemental Structural
Inspection Document, dated September 1989;
and Airbus Industrie Supplemental
Structural Inspection Document, Revision 2,
dated June 1994.
(3) Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for a
copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street, SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
E:\FR\FM\27FER1.SGM
27FER1
8608
Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
6, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–2512 Filed 2–26–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26044; Directorate
Identifier 2006–NM–098–AD; Amendment
39–14960; AD 2007–04–27]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.28 Mark 1000, 2000, 3000, and
4000 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
cprice-sewell on PROD1PC66 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Fokker Model F.28 Mark 1000, 2000,
3000, and 4000 airplanes. This AD
requires a one-time inspection of the
left- and right-hand main landing gear
(MLG) downlock actuators or a review
of the airplane maintenance records to
determine the part number of each
downlock actuator installed, and
replacement of identified MLG
downlock actuators with modified MLG
downlock actuators. This AD results
from a report of a failed downlock
actuator, which resulted in the left MLG
collapsing during taxi after landing. We
are issuing this AD to prevent failure of
the downlock actuator, which could
prevent the MLG side stay from locking
properly, resulting in collapse of the
MLG during ground maneuvers or upon
landing.
DATES: This AD becomes effective April
3, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of April 3, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Fokker Services B.V.,
Technical Services Dept., P.O. Box 231,
2150 AE Nieuw-Vennep, the
VerDate Aug<31>2005
16:09 Feb 26, 2007
Jkt 211001
Netherlands, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1137; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket 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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to all Fokker Model F.28 Mark
1000, 2000, 3000, and 4000 airplanes.
That NPRM was published in the
Federal Register on October 12, 2006
(71 FR 60085). That NPRM proposed to
require a one-time inspection of the leftand right-hand main landing gear (MLG)
downlock actuators or a review of the
airplane maintenance records to
determine the part number of each
downlock actuator installed, and
replacement of identified MLG
downlock actuators with modified MLG
downlock actuators.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To State Intent To Incorporate
Service Information
The Modification and Replacement
Parts Association (MARPA) requests
that, during the NPRM stage of AD
rulemaking, the FAA state its intent to
incorporate by reference (IBR) any
relevant service information. MARPA
states that without such a statement in
the NPRM, it is unclear whether the
relevant service information will be
incorporated by reference in the final
rule.
We do not agree with the commenter’s
request. When we reference certain
service information in a proposed AD,
the public can assume we intend to IBR
that service information, as required by
the Office of the Federal Register. No
PO 00000
Frm 00024
Fmt 4700
Sfmt 4700
change to this final rule is necessary in
regard to the commenter’s request.
Request To Incorporate Essential
Service Information
MARPA states that airworthiness
directives are frequently derived from
service information originating with the
type certificate holder or its suppliers.
MARPA further states that these
manufacturer service documents are
privately authored instruments
generally enjoying copyright protection
against duplication and publication.
MARPA asserts that when a service
document is incorporated by reference
into a public document, such as an AD,
it loses its private, protected status and
becomes a public document. MARPA
also states that if a service document is
used as a mandatory element of
compliance, it should not simply be
mentioned, but should be incorporated
into the regulatory document. Therefore,
MARPA states that it is concerned that
failure to incorporate the necessary
service information could result in a
court decision invalidating the AD. For
these reasons, MARPA requests that the
essential service documents be
incorporated by reference into the
regulatory instrument.
We understand MARPA’s comment
concerning IBR. The Office of the
Federal Register (OFR) requires that
documents that are necessary to
accomplish the requirements of the AD
be incorporated by reference during the
final rule phase of rulemaking. This
final rule incorporates by reference the
document necessary for the
accomplishment of the actions required
by this AD. Further, we point out that
while documents that are incorporated
by reference do become public
information, they do not lose their
copyright protection. For that reason,
we advise the public to contact the
manufacturer to obtain copies of the
referenced service information.
Request To Publish Service Information
on the Docket Management System
(DMS)
MARPA also requests that we make
service information available to the
public by publication in DMS, keyed to
the action that incorporates that
information. MARPA states that the
purpose of the IBR method is brevity, to
keep from expanding the Federal
Register needlessly by publishing
documents already available to the
affected individuals. MARPA asserts
that, traditionally, ‘‘affected
individuals’’ has meant aircraft owners
and operators who are generally
provided service information by the
manufacturer. MARPA further asserts
E:\FR\FM\27FER1.SGM
27FER1
]]>Agencies
[Federal Register Volume 72, Number 38 (Tuesday, February 27, 2007)]
[Rules and Regulations]
[Pages 8604-8608]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-2512]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25890; Directorate Identifier 2006-NM-115-AD;
Amendment 39-14943; AD 2007-04-11]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to all Airbus Model A300 B2, B4-100, and B4-200
series airplanes. That AD currently requires supplemental structural
inspections to detect fatigue cracking, and repair of cracked
structure. This new AD requires revising the maintenance program by
incorporating new and revised supplemental structural inspections,
inspection intervals, and repairs; and repair of any damaged, cracked,
or corroded structure; which would end the existing supplement
structural inspections. This AD results from a review of service
history and reports received from the current supplemental structural
inspection document program. We are issuing this AD to prevent reduced
structural integrity of these airplanes due to fatigue cracking.
DATES: This AD becomes effective April 3, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of April 3, 2007.
On August 9, 1996 (61 FR 35122, July 5, 1996), the Director of the
Federal Register approved the incorporation by reference of Airbus
Industrie Supplemental Structural Inspection Document, dated September
1989; and Airbus Industrie A300 Supplemental Structural Inspection
Document, Revision 2, dated June 1994.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
[[Page 8605]]
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket 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 street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 96-13-11, amendment 39-
9679 (61 FR 35122, July 5, 1996). The existing AD applies to all Airbus
Model A300 B2, B4-100, and B4-200 series airplanes. That NPRM was
published in the Federal Register on September 26, 2006 (71 FR 56058).
That NPRM proposed to continue to require supplemental structural
inspections to detect fatigue cracking, and repair of cracked
structure. That NPRM also proposed to require revising the maintenance
program by incorporating new and revised supplemental structural
inspections, inspection intervals, and repairs; and repair of any
damaged, cracked, or corroded structure; which would end the existing
supplement structural inspections.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received.
Request for Change to the Applicability
Airbus, the manufacturer, requests that we exclude the A300-600
series airplanes from the AD applicability. The commenter refers us to
page 1-A of Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Issue 3, dated September 2005, as revised by Airbus
Temporary Revision 3.1, dated April 2006, which does not include A300-
600 series airplanes.
We agree with the commenter's request. We do not want any reader of
this AD to infer that A300-600 series airplanes are included, and have
changed the applicability to exclude those airplanes in paragraph (c)
of this AD.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the change described previously.
We have determined that this change will neither increase the economic
burden on any operator nor increase the scope of the AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work Average labor Parts Cost per registered Fleet cost
hours rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Implementation of supplemental structural 597 $80 None........................ $47,760 29 $1,385,040
inspection program (required by AD 96-13-11).
Revision of the FAA-approved maintenance 10 80 None........................ 800 29 23,200
program (new 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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-9679 (61 FR 35122, July 5, 1996) and by adding
the following new airworthiness directive (AD):
2007-04-11 Airbus: Amendment 39-14943. Docket No. FAA-2006-25890;
Directorate Identifier 2006-NM-115-AD.
Effective Date
(a) This AD becomes effective April 3, 2007.
[[Page 8606]]
Affected ADs
(b) This AD supersedes AD 96-13-11.
Applicability
(c) This AD applies to all Airbus Model A300 B2 and B4 series
airplanes, certificated in any category, excluding A300-600 series
airplanes.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (x) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued damage tolerance of the affected structure. The FAA
has provided guidance for this determination in Advisory Circular
(AC) 25-1529.
Unsafe Condition
(d) This AD results from a review of service history and reports
received from the current supplemental structural inspection
document program. We are issuing this AD to prevent reduced
structural integrity of these airplanes due to fatigue cracking.
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.
Requirements of AD 96-13-11
(f) Within one year after March 9, 1993 (the effective date of
AD 93-01-24, amendment 39-8478), incorporate a revision into the
FAA-approved maintenance inspection program that provides for
supplemental maintenance inspections, modifications, repair, or
replacement of the significant structural details (SSD) and
significant structural items (SSI) specified in ``Airbus Industrie
A300 Supplemental Structural Inspection Document'' (SSID), dated
September 1989 (hereafter referred to as ``the SSID'').
(g) Within one year after August 9, 1996 (the effective date of
AD 96-13-11), replace the revision of the FAA-approved maintenance
program required by paragraph (f) of this AD with the inspections,
inspection intervals, repairs, and replacements defined in ``Airbus
Industrie A300 Supplemental Structural Inspection Document'' (SSID),
Revision 2, dated June 1994 (hereafter referred to as ``Revision 2
of the SSID''). Accomplish the actions specified in the service
bulletins identified in Section 6, ``SB Reference List,'' Revision 2
of the SSID, at the times specified in those service bulletins. The
actions are to be accomplished in accordance with those service
bulletins.
(1) For airplanes that have exceeded the threshold specified in
any of the service bulletins identified in Section 6, ``SB Reference
List,'' Revision 2 of the SSID: Accomplish the actions specified in
those service bulletins within the grace period specified in that
service bulletin. The grace period is to be measured from August 9,
1996.
(2) For airplanes that have exceeded the threshold specified in
any of the service bulletins identified in Section 6, ``SB Reference
List,'' Revision 2 of the SSID, and a grace period is not specified
in that service bulletin: Accomplish the actions specified in that
service bulletin within 1,500 flight cycles after August 9, 1996.
(h) If any cracked structure is detected during the inspections
required by either paragraph (f) or (g) of this AD, prior to further
flight, permanently repair the cracked structure in accordance with
either paragraph (h)(1), (h)(2), or (h)(3) of this AD.
Note 2: A permanent repair is defined as a repair that meets the
certification basis of the airplane, and does not require additional
modification at a later date.
(1) The service bulletins listed in Section 6, ``SB Reference
List,'' of the SSID (for airplanes that are currently being
inspected in accordance with paragraph (f) of this AD); or in
accordance with a method approved by the Manager, International
Branch, ANM-116 (formerly the Standardization Branch, ANM-113), FAA,
Transport Airplane Directorate, if a permanent repair is not
specified in any of these service bulletins. Or
(2) The service bulletins listed in Section 6, ``SB Reference
List,'' of Revision 2 of the SSID (for airplanes that are currently
being inspected in accordance with paragraph (g) of this AD); or in
accordance with a method approved by the Manager, International
Branch, ANM-116 (formerly the Standardization Branch, ANM-113), if a
permanent repair is not specified in any of these service bulletins.
Or,
(3) Other permanent repair data meeting the certification basis
of the airplane which is approved by the Manager, International
Branch, ANM-116 (formerly the Standardization Branch, ANM-113); or
by the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC)
of France.
(i) For airplanes identified as Fleet Leader Program (FLP) in
Section 5, ``Fleet Leader Program,'' of the SSID or Revision 2 of
the SSID: Inspect according to the instructions and intervals
specified in paragraph 4.4, ``Adjustment of Inspection Requirements
and DSG,'' of Section 4, or Section 9, as applicable, of the SSID
(for airplanes inspected in accordance with paragraph (f) of this
AD), or Revision 2 of the SSID (for airplanes inspected in
accordance with paragraph (g) of this AD), for each SSD.
(j) For the purpose of accomplishing paragraphs (i), (k), (l),
and (n) of this AD, operators shall not use paragraph 6.2,
``Complete RR Method,'' of Section 9 of the SSID to calculate
inspection thresholds and intervals.
(k) For Model A300-B2 and B2K-3C series airplanes: For any SSD
that has exceeded the values of the threshold specified in paragraph
6, ``Inspection Threshold and Intervals,'' Section 9 of the SSID,
inspect at the time specified in either paragraph (k)(1) or (k)(2)
of this AD, as applicable.
(1) For airplanes inspected in accordance with paragraph (f) of
this AD: Inspect within 2,000 landings after March 9, 1993, in
accordance with the SSID. Or,
(2) For airplanes inspected in accordance with paragraph (g) of
this AD: Inspect within 2,000 landings after August 9, 1996, in
accordance with Revision 2 of the SSID.
(l) For Model A300-B4 series airplanes: For any SSD that has
exceeded the values of the threshold specified in paragraph 6,
``Inspection Threshold and Intervals,'' Section 9 of the SSID,
inspect at the time specified in either paragraph (l)(1) or (l)(2)
of this AD, as applicable.
(1) For airplanes inspected in accordance with paragraph (f) of
this AD: Inspect within 1,500 landings after March 9, 1993 [the
effective date of AD 93-01-24, amendment 39-8478]. Or,
(2) For airplanes inspected in accordance with paragraph (g) of
this AD: Inspect within 1,500 landings after August 9, 1996.
(m) For airplanes identified as FLP in Section 5, ``Fleet Leader
Program,'' of the SSID or Revision 2 of the SSID: Within one year
after August 9, 1996, apply the basic requirements given in Revision
2 of the SSID.
(n) For airplanes that are subject to the requirements of
paragraph (g) of this AD, and have exceeded the initial inspection
threshold specified in paragraph 4.4, ``Adjustment of Inspection
Requirements and DSG,'' of Section 4, or paragraph 6, ``Inspection
Threshold and Intervals,'' of Section 9, for each SSD: Perform the
initial inspection prior to the accumulation of the number of flight
cycles specified in paragraph 7, ``Additional Information,'' Section
9, of Revision 2 of the SSID.
Note 3: Fatigue ratings are not applicable to these allowances;
therefore, no adjustment is required.
Note 4: Paragraph (n) of this AD provides the ``grace'' periods
for those airplanes that are new to the FLP or that have newly added
or revised SSID requirements in accordance with paragraph (g) of
this AD.
(o) The grace period provided by paragraph (n) of this AD is
also applicable to the thresholds and/or repeat intervals for each
SSD for which the inspection interval or threshold was reduced in
accordance with the requirements of paragraph (g) of this AD.
(p) For FLP airplanes identified in Section 5, ``Fleet Leader
Program,'' of the SSID or Revision 2 of the SSID that are listed in
Section 7, ``SSI Limitation List,'' of the SSID (for airplanes that
are currently being inspected in accordance with paragraph (f) of
this AD), or Revision 2 of the SSID (for airplanes that are
currently being inspected in accordance with paragraph (g) of this
AD): Inspect at intervals not to exceed the interval specified for
each SSI, in accordance with the values given in Section 7, ``SSI
Limitation List,'' of the SSID or Revision 2 of the SSID, as
applicable.
(q) For all airplanes: All inspection results, positive or
negative, must be reported to Airbus in accordance with either
paragraph (q)(1) or (q)(2) of this AD, as applicable. Information
collection requirements contained in this regulation 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.
[[Page 8607]]
3501 et seq.) and have been assigned OMB Control Number 2120-0056.
(1) For FLP airplanes, identified in Section 5, ``Fleet Leader
Program,'' of the SSID or Revision 2 of the SSID: Submit reports in
accordance with the instructions in paragraph 5.2, ``SSIP Inspection
Reporting,'' of Section 5, and paragraph 7.1, ``General,'' of
Section 7 of the SSID (for airplanes that are currently being
inspected in accordance with paragraph (f) of this AD); or Revision
2 of the SSID (for airplanes inspected in accordance with paragraph
(g) of this AD).
(2) For all airplanes that are subject to Section 6, ``SB
Reference List,'' of the SSID: Submit reports in accordance with the
instructions in the applicable service bulletins identified in
Section 6 of the SSID (for airplanes that are currently being
inspected in accordance with paragraph (f) of this AD); or Revision
2 of the SSID (for airplanes that are currently being inspected in
accordance with paragraph (g) of this AD).
New Requirements of This AD
Revision of the FAA-Approved Maintenance Inspection Program
(r) Within 12 months after the effective date of this AD,
replace the revision of the FAA-approved maintenance program
required by paragraph (g) of this AD with the supplemental
structural inspections, inspection intervals, and repairs defined in
Airbus A300 Airworthiness Limitation Items (ALI) Document SEM2/
95A.1090/05, Issue 3, dated September 2005, as revised by Airbus
Temporary Revision (TR) 3.1, dated April 2006 (hereafter referred to
as ``Issue 3 of the ALI''). Accomplish the actions specified in
Issue 3 of the ALI at the times specified in that ALI, except as
provided by paragraph (s) of this AD. The actions must be
accomplished in accordance with Issue 3 of the ALI. Accomplishing
the applicable initial ALI tasks constitutes terminating action for
the requirements of paragraphs (f) through (q) of this AD.
(s) For airplanes that have exceeded the threshold or intervals
specified in Issue 3 of the ALI for the application tolerance on the
first interval for new and revised requirements and have exceeded 50
percent of the intervals specified in sections D and E of Issue 3 of
the ALI: Do the actions within 6 months after the effective date of
this AD.
Corrective Actions
(t) Damaged, cracked, or corroded structure detected during any
inspection done in accordance with Issue 3 of the ALI must be
repaired, before further flight, in accordance with Issue 3 of the
ALI, except as provided by paragraph (u) of this AD; or other data
meeting the certification basis of the airplane which is approved by
the Manager, International Branch, ANM-116; or by the European
Aviation Safety Agency (EASA) (or its delegated agent).
(u) Where Issue 3 of the ALI specifies contacting Airbus for
appropriate action: Before further flight, repair the damaged,
cracked, or corroded structure using a method approved by either the
Manager, International Branch, ANM-116; or the EASA (or its
delegated agent).
No Fleet Sampling
(v) Although Issue 3 of the ALI specifies to do a ``Sampling
Concept'' in section B, this AD prohibits the use of such a sampling
program and requires all affected airplanes of the fleet to be
inspected.
No Reporting
(w) Although Issue 3 of the ALI specifies to submit certain
information to the manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance (AMOCs)
(x)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 96-13-11 are
approved as AMOCs for the corresponding provisions of paragraphs (f)
through (q) of this AD.
Related Information
(y) EASA airworthiness directive 2006-0071, dated March 30,
2006, also addresses the subject of this AD.
Material Incorporated by Reference
(z) You must use Airbus A300 Airworthiness Limitation Items
Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised
by Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Temporary Revision 3.1, including attachment, dated
April 2006, and including attachments dated September 2005; Airbus
Industrie Supplemental Structural Inspection Document, dated
September 1989; and Airbus Industrie A300 Supplemental Structural
Inspection Document, Revision 2, dated June 1994; as applicable, to
perform the actions that are required by this AD, unless the AD
specifies otherwise. Airbus A300 Airworthiness Limitation Items
Document SEM2/95A.1090/05, Issue 3, dated September 2005, contains
the following effective pages:
------------------------------------------------------------------------
Issue number shown
Page number on page Date shown on page
------------------------------------------------------------------------
1-SOC--10-SOC................... Section SOC, 3.... September 2005.
1-TOC........................... Section TOC, 3.... September 2005.
1-A............................. Section A, 3...... September 2005.
1-B--6-B........................ Section B, 3...... September 2005.
1-C, 2.......................... Section C, 3...... September 2005.
1-D, 2-D, 3-101................. Section D, 3...... September 2005.
1-E, 1-24....................... Section E, 3...... September 2005.
1-F, 2-39....................... Section F, 3...... September 2005.
1-G, 20-G, 30-G, 101-G.......... Section G, 3...... September 2005.
2-G--19-G, 21-G--29-G, 31-G-- 1................. January 2004.
100G, 102-G--328-G.
1-App--3-App.................... Section App, 3.... September 2005.
------------------------------------------------------------------------
(Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Issue 3, dated September 2005, contains two page 1-SOC
and two page 190-G. The first page identified as 1-SOC is the Record
of Changes and the second page 1-SOC is the first page of the
Summary of Changes. The first page identified as page 190-G refers
to Airworthiness Limitation Item 546014, and the second page 190-G
refers to Airworthiness Limitation Item 556001.) Airbus A300
Airworthiness Limitations Items Document SEM2/95A.1090/05, Temporary
Revision 3.1, dated April 2006, contains the following effective
pages:
------------------------------------------------------------------------
Issue number shown
Page number on page Date shown on page
------------------------------------------------------------------------
1-T.R. 3.1-4-T.R.3.1............ Original.......... April 2006.
Section D, 3-27................. T.R.3.1........... April 2006.
Section E, 1-4.................. 3................. September 2005.
Section F, 2-6.................. 3................. September 2005.
------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of Airbus A300 Airworthiness Limitation
Items Document SEM2/95A.1090/05, Issue 3, dated September 2005; as
revised by Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Temporary Revision 3.1, including attachment, dated
April 2006, and including attachments, dated September 2005; in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On August 9, 1996 (61 FR 35122, July 5, 1996), the Director
of the Federal Register approved the incorporation by reference of
Airbus Industrie Supplemental Structural Inspection Document, dated
September 1989; and Airbus Industrie Supplemental Structural
Inspection Document, Revision 2, dated June 1994.
(3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service information. You may
review copies at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_register/
[[Page 8608]]
code--of--federal--regulations/ibr--locations.html.
Issued in Renton, Washington, on February 6, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-2512 Filed 2-26-07; 8:45 am]
BILLING CODE 4910-13-P
