Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes; and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 33994-34000 [06-5244]
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33994
Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations
Restatement of Requirements of AD 99–12–
08
One-Time External Detailed Inspection
(f) Prior to the accumulation of 29,000 total
flight cycles or within 250 flight cycles after
August 9, 1993 (the effective date AD 93–13–
02, amendment 39–8615, which was
superseded by AD 99–12–08), whichever
occurs later, accomplish an external detailed
inspection to detect cracks of the fuselage
skin between stringers 19 left and 25 left and
at BS 360 to BS 540, in accordance with
Boeing Alert Service Bulletin 737–53A1160,
dated October 24, 1991; or Boeing Service
Bulletin 737–53A1160, Revision 1, dated
April 29, 1993. If any crack is found, prior
to further flight, accomplish the requirements
of paragraphs (f)(1) and (f)(2) of this AD.
(1) Perform an internal detailed inspection
to detect cracks of the frames between
stringers 19 left and 25 left and at BS 360 to
BS 500B, in accordance with either service
bulletin.
(2) Repair all cracks in accordance with a
method approved by the Manager, Seattle
Aircraft Certification Office (ACO), Transport
Airplane Directorate, FAA.
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Internal Detailed Inspections
(g) Within 3,000 flight cycles after
completing the requirements of paragraph (f)
of this AD, unless accomplished within the
last 6,000 flight cycles prior to August 9,
1993, perform an internal detailed inspection
to detect cracks of the frames between
stringers 19 left and 25 left and at body
stations 360 to 500B, in accordance with
Boeing Alert Service Bulletin 737–53A1160,
dated October 24, 1991; or Boeing Service
Bulletin 737–53A1160, Revision 1, dated
April 29, 1993. Thereafter, repeat the internal
detailed inspection at intervals not to exceed
9,000 flight cycles. If any crack is found
during any inspection required by this
paragraph, before further flight, repair as
specified in paragraph (g)(1) or (g)(2) of this
AD, as applicable.
(1) If any crack is found that does not
exceed the limits specified in the Boeing 737
Structural Repair Manual (SRM), repair the
crack in accordance with a method approved
by the Manager, Seattle ACO; or in
accordance with the procedures specified in
paragraph (k)(4) of this AD. The SRM is one
approved source of information for
accomplishing the requirements of this
paragraph. Repeat the internal detailed
inspection thereafter at intervals not to
exceed 9,000 flight cycles.
(2) If any crack is found that exceeds the
limits specified in the SRM, repair the crack
in accordance with a method approved by
the Manager, Seattle ACO; or in accordance
with the procedures specified in paragraph
(k)(4) of this AD. Repeat the internal detailed
visual inspection thereafter at intervals not to
exceed 9,000 flight cycles.
Install Doublers
(h) Prior to the accumulation of 75,000
total flight cycles, or within 3,000 flight
cycles after July 16, 1999 (the effective date
of AD 99–12–08), whichever occurs later,
install doublers on the specified frames
located between stringers 19 left and 25 left
from BS 360 to BS 500B, in accordance with
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Boeing Service Bulletin 737–53A1160,
Revision 1, dated April 29, 1993. Installing
these doublers on the specified fuselage
frames ends the repetitive inspections
required by paragraphs (f) and (g) of this AD.
New Requirements of This AD
Repetitive Inspection of Certain Frames
(i) Within 9,000 flight cycles after
accomplishing the modification required by
paragraph (h) of this AD, or within 4,500
flight cycles after the effective date of this
AD, whichever occurs later, perform an
internal detailed inspection to detect
cracking in the fuselage frame at BS 360 and
the fuselage frame at BS 500, between
stringers 19 left and 25 left, in accordance
with Boeing Alert Service Bulletin 737–
53A1160, dated October 24, 1991; or Boeing
Service Bulletin 737–53A1160, Revision 1,
dated April 29, 1993. Thereafter, repeat the
internal detailed inspection of the BS 360
and BS 500 frames at intervals not to exceed
9,000 flight cycles.
(j) If any crack is found during any
inspection required by paragraph (i) of this
AD, before further flight, repair the crack
using a method approved in accordance with
the procedures specified in paragraph (k) of
this AD.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle ACO, 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 14 CFR 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 99–12–08, including
AMOCs approved previously in accordance
with AD 93–13–02, are approved as AMOCs
for the corresponding provisions specified in
paragraphs (f), (g), and (h) of this AD.
(4) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Material Incorporated by Reference
(l) You must use Boeing Alert Service
Bulletin 737–53A1160, dated October 24,
1991; or Boeing Service Bulletin 737–
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Frm 00006
Fmt 4700
Sfmt 4700
53A1160, Revision 1, dated April 29, 1993,
as applicable, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of these documents on August 9,
1993 (58 FR 36863, July 9, 1993). Contact
Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124–2207, 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on June 5,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5287 Filed 6–12–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19002; Directorate
Identifier 2003–NM–27–AD; Amendment 39–
14639; AD 2006–12–13]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B2 and A300 B4 Series Airplanes;
A300 B4–600, B4–600R, and F4–600R
Series Airplanes; and Model C4–605R
Variant F Airplanes (Collectively Called
A300–600 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 certain Airbus Model
A300 and A300–600 series airplanes.
That AD currently requires repetitive
inspections to detect cracks in Gear Rib
5 of the main landing gear (MLG)
attachment fittings at the lower flange,
and repair, if necessary. That AD also
requires modification of Gear Rib 5 of
the MLG attachment fittings, which
constitutes terminating action for the
repetitive inspections. This new AD
requires new repetitive inspections at
reduced compliance times. This new
AD also requires new repetitive
inspections of certain areas of the
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mstockstill on PROD1PC61 with RULES
attachment fittings that were repaired in
accordance with the actions specified in
the existing AD. This AD results from
new service information that was issued
by the manufacturer and mandated by
the French airworthiness authority. We
are issuing this AD to prevent fatigue
cracking of the MLG attachment fittings,
which could result in reduced structural
integrity of the airplane.
DATES: This AD becomes effective July
18, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of July 18, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications, as listed in the
AD, on April 12, 2000 (65 FR 12077,
March 8, 2000).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications, as listed in
the AD, on October 20, 1999 (64 FR
49966, September 15, 1999).
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.
For Model A300 B2 and A300 B4
series airplanes, contact Jacques
Leborgne, Airbus Customer Service
Directorate, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
fax (+33) 5 61 93 36 14, for service
information identified in this AD. For
Model A300–600 series airplanes,
contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the street
address stated in the ADDRESSES section.
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Discussion
The FAA issued a supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that supersedes AD 2000–05–07,
amendment 39–11616 (65 FR 12077,
March 8, 2000), and applies to certain
Airbus Model A300 B2 and A300 B4
series airplanes; and Model A300–600
series airplanes. That supplemental
NPRM was published in the Federal
Register on March 27, 2006 (71 FR
15068). That supplemental NPRM
proposed to reduce the compliance
times for all inspections required by AD
2000–05–07; to require inspections in
accordance with new revisions of the
service bulletins; and to require new
repetitive inspections of certain areas of
the attachment fittings that were
repaired in accordance with the actions
specified in the existing AD.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Give Credit for Previous
Revisions of Certain Service Bulletins
Airbus states that Service Bulletins
A300–57–6088, Revision 03, dated
March 13, 2003; and A300–57–0235,
Revision 02, dated September 27, 1999;
are not referenced in Table 3 of the
supplemental NPRM for the terminating
modification. Airbus notes that these
service bulletins are listed in the
document index of Docket No. FAA–
2004–19002. Airbus reviewed the
technical content of these two service
bulletins and states that there is no
technical reason why they should not be
acceptable for complying with the
actions proposed in the supplemental
NPRM. Airbus therefore requests that
we include these service bulletins in
Table 3 of the final rule.
We partially agree. We agree that both
service bulletins are acceptable for
compliance with the corresponding
actions proposed in the supplemental
NPRM. We do not agree with adding
these service bulletins to Table 3 of the
final rule. Table 3 refers only to service
bulletins that were required by either
AD 2000–05–07 or the AD that it
superseded, which was AD 99–19–26,
amendment 39–11313 (64 FR 49966,
September 15, 1999); or that are the
latest revisions proposed for the
supplemental NPRM. Table 6 of the
supplemental NPRM refers to issues of
service bulletins that are not the latest
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Sfmt 4700
33995
revisions, and were not required by the
superseded ADs, but are still acceptable
for compliance. Both Airbus Service
Bulletin A300–57–6088, Revision 03,
and A300–57–0235, Revision 02, are
listed in Table 6 of the final rule. We
have not changed the final rule in this
regard.
Explanation of Editorial Changes to the
Final Rule
We inadvertently removed words
from the following paragraph of the
supplemental NPRM: ‘‘§ 39.13
[Amended] 2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD).’’ We have
changed this paragraph in the final rule
to include words that remove the
original NPRM as follows: ‘‘§ 39.13
[Amended] 2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–11616 (65
FR 12077, March 8, 2000), and adding
the following new airworthiness
directive (AD).’’
We have revised paragraph (i)(1) of
the final rule to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
Paragraphs (g)(2), (j)(2), (l), and (m) of
the supplemental NPRM specify making
repairs using a method approved by
´ ´
either the FAA or the Direction Generale
de l’Aviation Civile (DGAC) (or its
delegated agent). The European
Aviation Safety Agency (EASA) has
assumed responsibility for the airplane
models subject to this AD. Therefore, we
have revised paragraphs (g)(2), (j)(2), (l),
and (m) of the final rule to specify
making repairs using a method
approved by either the FAA or the
EASA (or its delegated agent).
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 changes described
previously. We have determined that
these changes 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.
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Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations
ESTIMATED COSTS
Action
Average labor
rate per hour
Work hours
Modification (required by AD 2000–05–
07) ........................................................
Pre-modification inspections (new action), per inspection cycle ....................
Post-modification inspections (new action), per inspection cycle ....................
Cost per
airplane
Parts
Number of
U.S.-cost
registered
airplanes
Fleet cost
70
$65
$10,270
$14,820
164
$2,430,480
6
65
(1)
2 390
164
2 63,960
2
65
(1)
2 130
164
221,320
1 None.
2 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 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
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 39–11616 (65
FR 12077, March 8, 2000), and adding
the following new airworthiness
directive (AD):
I
2006–12–13 Airbus: Amendment 39–14639.
Docket No. FAA–2004–19002;
Directorate Identifier 2003–NM–27–AD.
Effective Date
(a) This AD becomes effective July 18,
2006.
Affected ADs
(b) This AD supersedes AD 2000–05–07,
amendment 39–11616.
Applicability
(c) This AD applies to Airbus Model A300
B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–
103, and B4–203 airplanes, as identified in
Airbus Service Bulletin A300–57A0234,
Revision 05, dated February 19, 2002; and
Model A300 B4–601, B4–603, B4–620, B4–
622, B4–605R, B4–622R, F4–605R, F4–622R,
and C4–605R Variant F airplanes, as
identified in Airbus Service Bulletin A300–
57A6087, Revision 04, dated February 19,
2002; except airplanes on which Airbus
Modification 11912 or 11932 has been
installed; certificated in any category.
Unsafe Condition
(d) This AD was prompted by new service
information that was issued by the
manufacturer and mandated by the French
airworthiness authority. We are issuing this
AD to prevent fatigue cracking of the main
landing gear (MLG) attachment fittings,
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
the compliance times specified, unless the
actions have already been done.
Restatement of the Requirements of AD
2000–05–07
Repetitive Inspections
(f) Perform a detailed inspection and a
high-frequency eddy current (HFEC)
inspection to detect cracks in Gear Rib 5 of
the MLG attachment fittings at the lower
flange, in accordance with the
Accomplishment Instructions of any
applicable service bulletin listed in Table 1
and Table 2 of this AD, at the time specified
in paragraph (f)(1) or (f)(2) of this AD. After
April 12, 2000 (the effective date of AD
2000–05–07), only the service bulletins listed
in Table 2 of this AD may be used. Repeat
the inspections thereafter at intervals not to
exceed 1,500 flight cycles, until paragraph
(h), (i), or (k) of this AD is accomplished.
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TABLE 1.—REVISION 01 OF SERVICE BULLETINS
Model
Airbus Service
Bulletin
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R,
and A300 C4–605R Variant F airplanes.
A300–57–6087
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Revision level
01
13JNR1
Date
March 11, 1998.
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Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations
TABLE 1.—REVISION 01 OF SERVICE BULLETINS—Continued
Model
Airbus Service
Bulletin
A300 B2 and A300 B4 series airplanes ........................................................................
A300–57–0234
Revision level
01
Date
March 11, 1998.
TABLE 2.—FURTHER REVISIONS OF SERVICE BULLETINS
Model
Airbus Service
Bulletin
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, FA–605R, F4–622R,
and A300 C4–605R Variant F airplanes.
A300–57A6087
*02
June 24, 1999.
A300–57A0234
*03
*04
02
*03
*04
*05
May 19, 2000.
February 19, 2002.
June 24, 1999.
September 2, 1999.
May 19, 2000.
February 19, 2002.
A300 B2 and A300 B4 series airplanes ........................................................................
Revision level
Date
* Including Appendix 01.
(1) For airplanes that have accumulated
20,000 or more total flight cycles as of March
9, 1998 (the effective date of AD 98–03–06,
amendment 39–10298): Inspect within 500
flight cycles after March 9, 1998.
(2) For airplanes that have accumulated
less than 20,000 total flight cycles as of
March 9, 1998: Inspect prior to the
accumulation of 18,000 total flight cycles, or
within 1,500 flight cycles after March 9,
1998, whichever occurs later.
Note 1: For the purposes of this AD, a
detailed inspection is defined as: ‘‘An
intensive visual examination of a specific
structural area, system, installation, or
assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.’’
Note 2: Accomplishment of the initial
detailed and HFEC inspections in accordance
with Airbus Service Bulletin A300–57A0234
or A300–57A6087, both dated August 5,
1997, as applicable, is considered acceptable
for compliance with the initial inspections
required by paragraph (f) of this AD.
Repair
(g) If any crack is detected during any
inspection required by paragraph (f) of this
AD, prior to further flight, accomplish the
requirements of paragraph (g)(1) or (g)(2) of
this AD, as applicable.
(1) If a crack is detected at one hole only,
and the crack does not extend out of the
spotface of the hole, repair in accordance
with the Accomplishment Instructions of the
applicable service bulletin in Table 2 of this
AD.
(2) If a crack is detected at more than one
hole, or if any crack at any hole extends out
of the spotface of the hole, repair in
accordance with a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or
its delegated agent).
Terminating Modification
(h) Prior to the accumulation of 21,000
total flight cycles, or within 2 years after
October 20, 1999 (the effective date of AD
99–19–26, amendment 39–11313), whichever
occurs later: Modify Gear Rib 5 of the MLG
attachment fittings at the lower flange in
accordance with the Accomplishment
Instructions of the applicable service bulletin
in Table 3 of this AD. After the effective date
of this AD, only Revision 04 of Airbus
Service Bulletin A300–57–6088, and
Revisions 04 and 05 of Airbus Service
Bulletin A300–57–0235 may be used.
Accomplishment of this modification
constitutes terminating action for the
repetitive inspection requirements of
paragraphs (f) and (i) of this AD.
TABLE 3.—SERVICE BULLETINS FOR TERMINATING MODIFICATION
Model
Airbus Service
Bulletin
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R,
A300 C4–605R Variant F airplanes.
A300–57–6088
A300 B2 and A300 B4 series airplanes ........................................................................
Revision level
Date
* 01
02
04
* 01
03
04
05
A300–57–0235
February 1, 1999.
September 5, 2002.
December 3, 2003.
February 1, 1999.
September 5, 2002.
March 13, 2003.
December 3, 2003.
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* Including Appendix 01.
Note 3: Accomplishment of the
modification required by paragraph (h) of
this AD prior to April 12, 2000, in
accordance with Airbus Service Bulletin
A300–57–6088 or A300–57–0235, both dated
August 5, 1998; as applicable; is acceptable
for compliance with the requirements of that
paragraph.
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New Requirements of This AD
New Repetitive Inspections
(i) For airplanes on which the modification
specified in paragraph (h) or (k) of this AD
has not been done as of the effective date of
this AD, perform a detailed and an HFEC
inspection to detect cracks of the lower
flange of Gear Rib 5 of the MLG at holes 43,
47, 48, 49, 50, 52, and 54, in accordance with
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Sfmt 4700
the applicable service bulletin listed in Table
4 of this AD. Perform the inspections at the
applicable time specified in paragraph (i)(1),
(i)(2), (i)(3), or (i)(4) of this AD. Repeat the
inspections thereafter at intervals not to
exceed 700 flight cycles until the terminating
modification required by paragraph (k) of this
AD is accomplished. Accomplishment of the
inspections per paragraph (i) of this AD,
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terminates the inspection requirements of
paragraph (f) of this AD.
TABLE 4.—SERVICE BULLETINS FOR REPETITIVE INSPECTIONS
Model
Airbus Service
Bulletin
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R,
and C4–605R Variant F airplanes.
A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes ......
A300–57A6087
* 04
February 19, 2002.
A300–57A0234
* 05
February 19, 2002.
Revision level
Date
* Including Appendix 01.
(1) For Model A300 B2–1A, B2–1C, B2K–
3C, B2–203, B4–2C, B4–103, and B4–203
airplanes; Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R, F4–605R,
F4–622R, and C4–605R Variant F airplanes;
and Model C4–605R Variant F airplanes that
have accumulated 18,000 or more total flight
cycles as of the effective date of this AD:
Within 700 flight cycles after the effective
date of this AD.
(2) For Model A300 B2–1A, B2–1C, B2K–
3C, and B2–203 airplanes that have
accumulated less than 18,000 total flight
cycles as of the effective date of this AD:
Prior to the accumulation of 18,000 total
flight cycles, or within 700 flight cycles after
the effective date of this AD, whichever
occurs later.
(3) For Model A300 B4–2C, B4–103, and
B4–203 airplanes that have accumulated less
than 18,000 total flight cycles as of the
effective date of this AD: Prior to the
accumulation of 14,500 total flight cycles, or
within 700 flight cycles after the effective
date of this AD, whichever occurs later.
(4) For Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R, F4–605R,
F4–622R, and C4–605R Variant F airplanes
that have accumulated less than 18,000 total
flight cycles as of the effective date of this
AD: Prior to the accumulation of 11,600 total
flight cycles, or within 700 flight cycles after
the effective date of this AD, whichever
occurs later.
(2) If a crack is detected at more than one
hole, or if any crack at any hole extends out
of the spotface of the hole, repair in
accordance with a method approved by the
Manager, International Branch, ANM–116, or
the EASA (or its delegated agent).
Crack Repair
(j) If any crack is detected during any
inspection required by paragraph (i) of this
AD, prior to further flight, accomplish the
requirements of paragraph (j)(1) and (j)(2) of
this AD, as applicable.
(1) If a crack is detected at only one hole,
and the crack does not extend out of the
spotface of the hole, repair in accordance
with Airbus Service Bulletin A300–57A0234,
Revision 05, including Appendix 01, dated
February 19, 2002 (for Model A300 B2–1A,
B2–1C, B2K–3C, B2–203, B4–2C, B4–103,
and B4–203 airplanes); or A300–57A6087,
Revision 04, including Appendix 01, dated
February 19, 2002 (for Model A300 B4–601,
B4–603, B4–620, B4–622, B4–605R, B4–
622R, F4–605R, F4–622R, and C4–605R
airplanes); as applicable.
(k) For airplanes on which the terminating
modification in paragraph (h) of this AD has
not been accomplished before the effective
date of this AD: At the earlier of the times
specified in paragraphs (k)(1) and (k)(2) of
this AD, modify Gear Rib 5 of the MLG
attachment fittings at the lower flange.
Except as provided by paragraph letter (l) of
this AD, do the modification in accordance
with the applicable service bulletin in Table
5 of this AD. This action terminates the
repetitive inspections requirements of
paragraphs (f) and (i) of this AD.
(1) Prior to the accumulation of 21,000
total flight cycles, or within 2 years after
October 20, 1999, whichever is later.
(2) Within 16 months after the effective
date of this AD.
Terminating Modification
TABLE 5.—SERVICE BULLETINS FOR TERMINATING MODIFICATION
Model
Airbus Service
Bulletin
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R,
and C4–605R Variant F airplanes.
A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 05 2003 airplanes.
A300–57–6088
04
December 3, 2003.
A300–57–0235
04
05
March 13, 2003.
December 3, 2003.
mstockstill on PROD1PC61 with RULES
(l) Where the applicable service bulletin in
paragraph (k) of this AD specifies to contact
Airbus for modification instructions; or if
there is a previously installed repair at any
of the affected fastener holes; or if a crack is
found when accomplishing the modification:
Prior to further flight, modify in accordance
with a method approved by the Manager,
International Branch, ANM–116, or the
EASA (or its delegated agent).
Post-Modification Inspections
(m) Within 700 flight cycles after doing the
modification in accordance with paragraph
(h), (k), or (l) of this AD, or within 6 months
after the effective date of this AD, whichever
occurs later, except as provided by paragraph
(o) of this AD: Do a detailed and an HFEC
inspection for cracks at holes 47 and 54 in
VerDate Aug<31>2005
14:46 Jun 12, 2006
Jkt 208001
the lower flange of Gear Rib 5, and do all
related investigative and corrective actions
before further flight, by doing all the actions
specified in the Accomplishment
Instructions of Airbus Service Bulletin A300–
57A0246, including Appendix 01, dated May
20, 2005; or Airbus Service Bulletin A300–
57A6101, including Appendix 01, dated May
20, 2005; as applicable. Where the applicable
service bulletin specifies to contact Airbus
for repair instructions: Prior to further flight,
modify in accordance with a method
approved by the Manager, International
Branch, ANM–116, or the EASA (or its
delegated agent). Repeat the inspection and
related investigative and corrective actions
thereafter at intervals not to exceed 700 flight
cycles. If no crack is detected during the
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
Revision level
Date
repeat inspection performed at or above
2,100 flight cycles after doing the
modification in accordance with paragraph
(h), (k), or (l) of this AD, then no further
inspection is required. Except, at least one
inspection is required after the accumulation
of 2,100 flight cycles after installing the
modification in accordance with paragraph
(h) or (k) of this AD.
Actions Accomplished Per Previous Issues of
the Service Bulletins
(n) Actions accomplished before the
effective date of this AD, per the service
bulletins listed in Table 6 of this AD, are
considered acceptable for compliance with
the corresponding action specified in this
AD.
E:\FR\FM\13JNR1.SGM
13JNR1
33999
Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations
TABLE 6.—PREVIOUS ISSUES OF SERVICE BULLETINS
Airbus Service Bulletin
Revision level
A300–57–0235 .............................................................................................................................................
* 02
A300–57–6088 .............................................................................................................................................
03
02
03
Date
September 27, 1999.
September 5, 2002.
September 5, 2000.
March 13, 2003.
* Including Appendix 01.
Reporting
(o)(1) Although Airbus Service Bulletins
A300–57A0234, A300–57–0235, A300–
57A6087, A300–57–6088, A300–57A0246,
and A300–57A6101, specify to submit certain
information to the manufacturer, this AD
does not include such a requirement, except
as provided by paragraph (o)(2) of this AD.
(2) Where Airbus Service Bulletins A300–
57A0246 and A300–57A6101 specify to
submit a report of positive and negative
findings of the post-modification inspection
required by paragraph (m) of this AD, within
30 days after the effective date of this AD,
submit a report only of the positive findings
of post-modification inspections to Airbus,
Customer Service Directorate, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France. The report must include the
inspection results, a description of any
discrepancies found, the airplane serial
number, and the number of landings and
flight hours on the airplane. Under the
provisions of the Paperwork Reduction Act of
1980 (44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
Alternative Methods of Compliance
(AMOCs)
(p)(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 per AD
2000–05–07 are approved as AMOCs with
this AD.
Related Information
(q) French airworthiness directives 2003–
318(B), dated August 20, 2003; and F–2005–
113 R1, dated July 20, 2005; also address the
subject of this AD.
Material Incorporated by Reference
(r) You must use the service information
listed in Table 7 of this AD to perform the
actions that are required by this AD, unless
the AD specifies otherwise.
TABLE 7.—MATERIAL INCORPORATED BY REFERENCE
Revision
level
Airbus Service Bulletin
A300–57A0234
A300–57A0234
A300–57A0234
A300–57A0234
A300–57A0246
A300–57A6087
A300–57A6087
A300–57A6087
A300–57A6101
A300–57–0234
A300–57–0235
A300–57–0235
A300–57–0235
A300–57–0235
A300–57–6087
A300–57–6088
A300–57–6088
A300–57–6088
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
02 ...............
* 03 ..............
* 04 ..............
* 05 ..............
Original * ......
* 02 ..............
* 03 ..............
* 04 ..............
Original * ......
01 ...............
* 01 ..............
03 ...............
04 ...............
05 ...............
01 ...............
* 01 ..............
02 ...............
04 ...............
Date
June 24, 1999.
September 2, 1999.
May 19, 2000.
February 19, 2002.
May 20, 2005.
June 24, 1999.
May 19, 2000.
February 19, 2002.
May 20, 2005.
March 11, 1998.
February 1, 1999.
September 5, 2002.
March 13, 2003.
December 3, 2003.
March 11, 1998.
February 1, 1999.
September 5, 2002.
December 3, 2003.
* Including Appendix 01.
(1) The Director of the Federal Register
approved the incorporation by reference of
the documents listed in Table 8 of this AD
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
TABLE 8.—NEW MATERIAL INCORPORATED BY REFERENCE
Revision
level
mstockstill on PROD1PC61 with RULES
Airbus Service Bulletin
A300–57A0234
A300–57A0234
A300–57A0246
A300–57A6087
A300–57A6087
A300–57A6101
A300–57–0235
A300–57–0235
VerDate Aug<31>2005
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
15:19 Jun 12, 2006
Jkt 208001
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
E:\FR\FM\13JNR1.SGM
* 04 ..............
* 05 ..............
Original * ......
* 03 ..............
* 04 ..............
Original * ......
03 ...............
04 ...............
13JNR1
Date
May 19, 2000.
February 19, 2002.
May 20, 2005.
May 19, 2000.
February 19, 2002.
May 20, 2005.
September 5, 2002.
March 13, 2003.
34000
Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations
TABLE 8.—NEW MATERIAL INCORPORATED BY REFERENCE—Continued
Airbus Service Bulletin
Revision
level
A300–57–0235 ...............................................................................................................................................
A300–57–6088 ...............................................................................................................................................
A300–57–6088 ...............................................................................................................................................
05 ...............
02 ...............
04 ...............
Date
December 3, 2003.
September 5, 2002.
December 3, 2003.
* Including Appendix 01.
(2) On April 12, 2000 (65 FR 12077, March
8, 2000), the Director of the Federal Register
approved the incorporation by reference of
the documents listed in Table 9 of this AD.
TABLE 9.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Airbus Service Bulletin
Revision level
A300–57A0234 ............................................................................................................................................
A300–57A0234 ............................................................................................................................................
A300–57A6087 ............................................................................................................................................
02
* 03
* 02
Date
June 24, 1999.
September 2, 1999.
June 24, 1999.
* Including Appendix 01.
(3) On October 20, 1999 (64 FR 49966,
September 15, 1999), the Director of the
Federal Register approved the incorporation
by reference of the documents listed in Table
10 of this AD.
TABLE 10.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Airbus Service Bulletin
A300–57–0234
A300–57–0235
A300–57–6087
A300–57–6088
Revision level
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
01
* 01
01
* 01
Date
March 11, 1998.
February 1, 1999.
March 11, 1998.
February 1, 1999.
* Including Appendix 01.
(4) 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on May 31,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5244 Filed 6–12–06; 8:45 am]
mstockstill on PROD1PC61 with RULES
14:46 Jun 12, 2006
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24076; Directorate
Identifier 2006–NM–015–AD; Amendment
39–14640; AD 2006–12–14]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira del Aeronautica S.A.
(EMBRAER) Model EMB–120, –120ER,
–120FC, –120QC, and –120RT
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
EMBRAER Model EMB–120, –120ER,
–120FC, –120QC, and –120RT airplanes.
This AD requires replacing the shut-off
and crossbleed valves of the bleed air
system with new valves having
hermetically sealed switches. This AD
results from fuel system reviews
conducted by the manufacturer. We are
BILLING CODE 4910–13–P
VerDate Aug<31>2005
DEPARTMENT OF TRANSPORTATION
Jkt 208001
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
issuing this AD to prevent a potential
source of ignition near a fuel tank,
which, in combination with flammable
fuel vapors, could result in a fuel tank
explosion and consequent loss of the
airplane.
DATES: This AD becomes effective July
18, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of July 18, 2006.
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 Empresa Brasileira de
Aeronautica S.A. (EMBRAER), P.O. Box
343—CEP 12.225, Sao Jose dos
Campos—SP, Brazil, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
fax (425) 227–1149.
E:\FR\FM\13JNR1.SGM
13JNR1
]]>Agencies
[Federal Register Volume 71, Number 113 (Tuesday, June 13, 2006)]
[Rules and Regulations]
[Pages 33994-34000]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5244]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19002; Directorate Identifier 2003-NM-27-AD;
Amendment 39-14639; AD 2006-12-13]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series
Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes; and
Model C4-605R Variant F Airplanes (Collectively Called A300-600 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 certain Airbus Model A300 and A300-600 series
airplanes. That AD currently requires repetitive inspections to detect
cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings
at the lower flange, and repair, if necessary. That AD also requires
modification of Gear Rib 5 of the MLG attachment fittings, which
constitutes terminating action for the repetitive inspections. This new
AD requires new repetitive inspections at reduced compliance times.
This new AD also requires new repetitive inspections of certain areas
of the
[[Page 33995]]
attachment fittings that were repaired in accordance with the actions
specified in the existing AD. This AD results from new service
information that was issued by the manufacturer and mandated by the
French airworthiness authority. We are issuing this AD to prevent
fatigue cracking of the MLG attachment fittings, which could result in
reduced structural integrity of the airplane.
DATES: This AD becomes effective July 18, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of July 18, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications, as listed in the AD, on April 12,
2000 (65 FR 12077, March 8, 2000).
The Director of the Federal Register approved the incorporation by
reference of certain other publications, as listed in the AD, on
October 20, 1999 (64 FR 49966, September 15, 1999).
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.
For Model A300 B2 and A300 B4 series airplanes, contact Jacques
Leborgne, Airbus Customer Service Directorate, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, fax (+33) 5 61 93 36 14, for
service information identified in this AD. For Model A300-600 series
airplanes, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the AD docket on the Internet at https://dms.dot.gov
or in person at the Docket Management Facility office between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays. The Docket
Management Facility office (telephone (800) 647-5227) is located on the
plaza level of the Nassif Building at the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a supplemental notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an AD that supersedes AD 2000-05-07,
amendment 39-11616 (65 FR 12077, March 8, 2000), and applies to certain
Airbus Model A300 B2 and A300 B4 series airplanes; and Model A300-600
series airplanes. That supplemental NPRM was published in the Federal
Register on March 27, 2006 (71 FR 15068). That supplemental NPRM
proposed to reduce the compliance times for all inspections required by
AD 2000-05-07; to require inspections in accordance with new revisions
of the service bulletins; and to require new repetitive inspections of
certain areas of the attachment fittings that were repaired in
accordance with the actions specified in the existing AD.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Give Credit for Previous Revisions of Certain Service
Bulletins
Airbus states that Service Bulletins A300-57-6088, Revision 03,
dated March 13, 2003; and A300-57-0235, Revision 02, dated September
27, 1999; are not referenced in Table 3 of the supplemental NPRM for
the terminating modification. Airbus notes that these service bulletins
are listed in the document index of Docket No. FAA-2004-19002. Airbus
reviewed the technical content of these two service bulletins and
states that there is no technical reason why they should not be
acceptable for complying with the actions proposed in the supplemental
NPRM. Airbus therefore requests that we include these service bulletins
in Table 3 of the final rule.
We partially agree. We agree that both service bulletins are
acceptable for compliance with the corresponding actions proposed in
the supplemental NPRM. We do not agree with adding these service
bulletins to Table 3 of the final rule. Table 3 refers only to service
bulletins that were required by either AD 2000-05-07 or the AD that it
superseded, which was AD 99-19-26, amendment 39-11313 (64 FR 49966,
September 15, 1999); or that are the latest revisions proposed for the
supplemental NPRM. Table 6 of the supplemental NPRM refers to issues of
service bulletins that are not the latest revisions, and were not
required by the superseded ADs, but are still acceptable for
compliance. Both Airbus Service Bulletin A300-57-6088, Revision 03, and
A300-57-0235, Revision 02, are listed in Table 6 of the final rule. We
have not changed the final rule in this regard.
Explanation of Editorial Changes to the Final Rule
We inadvertently removed words from the following paragraph of the
supplemental NPRM: ``Sec. 39.13 [Amended] 2. The Federal Aviation
Administration (FAA) amends Sec. 39.13 by adding the following new
airworthiness directive (AD).'' We have changed this paragraph in the
final rule to include words that remove the original NPRM as follows:
``Sec. 39.13 [Amended] 2. The Federal Aviation Administration (FAA)
amends Sec. 39.13 by removing amendment 39-11616 (65 FR 12077, March
8, 2000), and adding the following new airworthiness directive (AD).''
We have revised paragraph (i)(1) of the final rule to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Paragraphs (g)(2), (j)(2), (l), and (m) of the supplemental NPRM
specify making repairs using a method approved by either the FAA or the
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its
delegated agent). The European Aviation Safety Agency (EASA) has
assumed responsibility for the airplane models subject to this AD.
Therefore, we have revised paragraphs (g)(2), (j)(2), (l), and (m) of
the final rule to specify making repairs using a method approved by
either the FAA or the EASA (or its delegated agent).
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 changes described previously.
We have determined that these changes 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.
[[Page 33996]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Average labor Cost per cost
Action Work hours rate per hour Parts airplane registered Fleet cost
airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification (required by AD 2000-05-07)................ 70 $65 $10,270 $14,820 164 $2,430,480
Pre-modification inspections (new action), per 6 65 (1) 2 390 164 2 63,960
inspection cycle.......................................
Post-modification inspections (new action), per 2 65 (1) 2 130 164 221,320
inspection cycle.......................................
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ None.
\2\ 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 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 39-11616 (65 FR 12077, March 8, 2000), and adding
the following new airworthiness directive (AD):
2006-12-13 Airbus: Amendment 39-14639. Docket No. FAA-2004-19002;
Directorate Identifier 2003-NM-27-AD.
Effective Date
(a) This AD becomes effective July 18, 2006.
Affected ADs
(b) This AD supersedes AD 2000-05-07, amendment 39-11616.
Applicability
(c) This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C,
B2-203, B4-2C, B4-103, and B4-203 airplanes, as identified in Airbus
Service Bulletin A300-57A0234, Revision 05, dated February 19, 2002;
and Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-
605R, F4-622R, and C4-605R Variant F airplanes, as identified in
Airbus Service Bulletin A300-57A6087, Revision 04, dated February
19, 2002; except airplanes on which Airbus Modification 11912 or
11932 has been installed; certificated in any category.
Unsafe Condition
(d) This AD was prompted by new service information that was
issued by the manufacturer and mandated by the French airworthiness
authority. We are issuing this AD to prevent fatigue cracking of the
main landing gear (MLG) attachment fittings, 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 the compliance times specified, unless the
actions have already been done.
Restatement of the Requirements of AD 2000-05-07
Repetitive Inspections
(f) Perform a detailed inspection and a high-frequency eddy
current (HFEC) inspection to detect cracks in Gear Rib 5 of the MLG
attachment fittings at the lower flange, in accordance with the
Accomplishment Instructions of any applicable service bulletin
listed in Table 1 and Table 2 of this AD, at the time specified in
paragraph (f)(1) or (f)(2) of this AD. After April 12, 2000 (the
effective date of AD 2000-05-07), only the service bulletins listed
in Table 2 of this AD may be used. Repeat the inspections thereafter
at intervals not to exceed 1,500 flight cycles, until paragraph (h),
(i), or (k) of this AD is accomplished.
Table 1.--Revision 01 of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, B4- A300-57-6087 01 March 11, 1998.
605R, B4-622R, F4-605R, F4-622R, and
A300 C4-605R Variant F airplanes.
[[Page 33997]]
A300 B2 and A300 B4 series airplanes.... A300-57-0234 01 March 11, 1998.
----------------------------------------------------------------------------------------------------------------
Table 2.--Further Revisions of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, B4- A300-57A6087 *02 June 24, 1999.
605R, B4-622R, FA-605R, F4-622R, and
A300 C4-605R Variant F airplanes.
............... *03 May 19, 2000.
............... *04 February 19, 2002.
A300 B2 and A300 B4 series airplanes.... A300-57A0234 02 June 24, 1999.
............... *03 September 2, 1999.
............... *04 May 19, 2000.
............... *05 February 19, 2002.
----------------------------------------------------------------------------------------------------------------
* Including Appendix 01.
(1) For airplanes that have accumulated 20,000 or more total
flight cycles as of March 9, 1998 (the effective date of AD 98-03-
06, amendment 39-10298): Inspect within 500 flight cycles after
March 9, 1998.
(2) For airplanes that have accumulated less than 20,000 total
flight cycles as of March 9, 1998: Inspect prior to the accumulation
of 18,000 total flight cycles, or within 1,500 flight cycles after
March 9, 1998, whichever occurs later.
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
Note 2: Accomplishment of the initial detailed and HFEC
inspections in accordance with Airbus Service Bulletin A300-57A0234
or A300-57A6087, both dated August 5, 1997, as applicable, is
considered acceptable for compliance with the initial inspections
required by paragraph (f) of this AD.
Repair
(g) If any crack is detected during any inspection required by
paragraph (f) of this AD, prior to further flight, accomplish the
requirements of paragraph (g)(1) or (g)(2) of this AD, as
applicable.
(1) If a crack is detected at one hole only, and the crack does
not extend out of the spotface of the hole, repair in accordance
with the Accomplishment Instructions of the applicable service
bulletin in Table 2 of this AD.
(2) If a crack is detected at more than one hole, or if any
crack at any hole extends out of the spotface of the hole, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or its delegated agent).
Terminating Modification
(h) Prior to the accumulation of 21,000 total flight cycles, or
within 2 years after October 20, 1999 (the effective date of AD 99-
19-26, amendment 39-11313), whichever occurs later: Modify Gear Rib
5 of the MLG attachment fittings at the lower flange in accordance
with the Accomplishment Instructions of the applicable service
bulletin in Table 3 of this AD. After the effective date of this AD,
only Revision 04 of Airbus Service Bulletin A300-57-6088, and
Revisions 04 and 05 of Airbus Service Bulletin A300-57-0235 may be
used. Accomplishment of this modification constitutes terminating
action for the repetitive inspection requirements of paragraphs (f)
and (i) of this AD.
Table 3.--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, B4- A300-57-6088 \*\ 01 February 1, 1999.
605R, B4-622R, F4-605R, F4-622R, A300
C4-605R Variant F airplanes.
............... 02 September 5, 2002.
............... 04 December 3, 2003.
A300 B2 and A300 B4 series airplanes.... A300-57-0235 \*\ 01 February 1, 1999.
............... 03 September 5, 2002.
............... 04 March 13, 2003.
............... 05 December 3, 2003.
----------------------------------------------------------------------------------------------------------------
* Including Appendix 01.
Note 3: Accomplishment of the modification required by paragraph
(h) of this AD prior to April 12, 2000, in accordance with Airbus
Service Bulletin A300-57-6088 or A300-57-0235, both dated August 5,
1998; as applicable; is acceptable for compliance with the
requirements of that paragraph.
New Requirements of This AD
New Repetitive Inspections
(i) For airplanes on which the modification specified in
paragraph (h) or (k) of this AD has not been done as of the
effective date of this AD, perform a detailed and an HFEC inspection
to detect cracks of the lower flange of Gear Rib 5 of the MLG at
holes 43, 47, 48, 49, 50, 52, and 54, in accordance with the
applicable service bulletin listed in Table 4 of this AD. Perform
the inspections at the applicable time specified in paragraph
(i)(1), (i)(2), (i)(3), or (i)(4) of this AD. Repeat the inspections
thereafter at intervals not to exceed 700 flight cycles until the
terminating modification required by paragraph (k) of this AD is
accomplished. Accomplishment of the inspections per paragraph (i) of
this AD,
[[Page 33998]]
terminates the inspection requirements of paragraph (f) of this AD.
Table 4.--Service Bulletins for Repetitive Inspections
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, B4- A300-57A6087 \*\ 04 February 19, 2002.
605R, B4-622R, F4-605R, F4-622R, and C4-
605R Variant F airplanes.
A300 B2-1A, B2-1C, B2K-3C, B2-203, B4- A300-57A0234 \*\ 05 February 19, 2002.
2C, B4-103, and B4-203 airplanes.
----------------------------------------------------------------------------------------------------------------
* Including Appendix 01.
(1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103,
and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes;
and Model C4-605R Variant F airplanes that have accumulated 18,000
or more total flight cycles as of the effective date of this AD:
Within 700 flight cycles after the effective date of this AD.
(2) For Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes
that have accumulated less than 18,000 total flight cycles as of the
effective date of this AD: Prior to the accumulation of 18,000 total
flight cycles, or within 700 flight cycles after the effective date
of this AD, whichever occurs later.
(3) For Model A300 B4-2C, B4-103, and B4-203 airplanes that have
accumulated less than 18,000 total flight cycles as of the effective
date of this AD: Prior to the accumulation of 14,500 total flight
cycles, or within 700 flight cycles after the effective date of this
AD, whichever occurs later.
(4) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes that have
accumulated less than 18,000 total flight cycles as of the effective
date of this AD: Prior to the accumulation of 11,600 total flight
cycles, or within 700 flight cycles after the effective date of this
AD, whichever occurs later.
Crack Repair
(j) If any crack is detected during any inspection required by
paragraph (i) of this AD, prior to further flight, accomplish the
requirements of paragraph (j)(1) and (j)(2) of this AD, as
applicable.
(1) If a crack is detected at only one hole, and the crack does
not extend out of the spotface of the hole, repair in accordance
with Airbus Service Bulletin A300-57A0234, Revision 05, including
Appendix 01, dated February 19, 2002 (for Model A300 B2-1A, B2-1C,
B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or A300-
57A6087, Revision 04, including Appendix 01, dated February 19, 2002
(for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R,
F4-605R, F4-622R, and C4-605R airplanes); as applicable.
(2) If a crack is detected at more than one hole, or if any
crack at any hole extends out of the spotface of the hole, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, or the EASA (or its delegated agent).
Terminating Modification
(k) For airplanes on which the terminating modification in
paragraph (h) of this AD has not been accomplished before the
effective date of this AD: At the earlier of the times specified in
paragraphs (k)(1) and (k)(2) of this AD, modify Gear Rib 5 of the
MLG attachment fittings at the lower flange. Except as provided by
paragraph letter (l) of this AD, do the modification in accordance
with the applicable service bulletin in Table 5 of this AD. This
action terminates the repetitive inspections requirements of
paragraphs (f) and (i) of this AD.
(1) Prior to the accumulation of 21,000 total flight cycles, or
within 2 years after October 20, 1999, whichever is later.
(2) Within 16 months after the effective date of this AD.
Table 5.--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, B4- A300-57-6088 04 December 3, 2003.
605R, B4-622R, F4-605R, F4-622R, and C4-
605R Variant F airplanes.
A300 B2-1A, B2-1C, B2K-3C, B2-203, B4- A300-57-0235 04 March 13, 2003.
2C, B4-103, and B4-203 05 2003 05 December 3, 2003.
airplanes.
----------------------------------------------------------------------------------------------------------------
(l) Where the applicable service bulletin in paragraph (k) of
this AD specifies to contact Airbus for modification instructions;
or if there is a previously installed repair at any of the affected
fastener holes; or if a crack is found when accomplishing the
modification: Prior to further flight, modify in accordance with a
method approved by the Manager, International Branch, ANM-116, or
the EASA (or its delegated agent).
Post-Modification Inspections
(m) Within 700 flight cycles after doing the modification in
accordance with paragraph (h), (k), or (l) of this AD, or within 6
months after the effective date of this AD, whichever occurs later,
except as provided by paragraph (o) of this AD: Do a detailed and an
HFEC inspection for cracks at holes 47 and 54 in the lower flange of
Gear Rib 5, and do all related investigative and corrective actions
before further flight, by doing all the actions specified in the
Accomplishment Instructions of Airbus Service Bulletin A300-57A0246,
including Appendix 01, dated May 20, 2005; or Airbus Service
Bulletin A300-57A6101, including Appendix 01, dated May 20, 2005; as
applicable. Where the applicable service bulletin specifies to
contact Airbus for repair instructions: Prior to further flight,
modify in accordance with a method approved by the Manager,
International Branch, ANM-116, or the EASA (or its delegated agent).
Repeat the inspection and related investigative and corrective
actions thereafter at intervals not to exceed 700 flight cycles. If
no crack is detected during the repeat inspection performed at or
above 2,100 flight cycles after doing the modification in accordance
with paragraph (h), (k), or (l) of this AD, then no further
inspection is required. Except, at least one inspection is required
after the accumulation of 2,100 flight cycles after installing the
modification in accordance with paragraph (h) or (k) of this AD.
Actions Accomplished Per Previous Issues of the Service Bulletins
(n) Actions accomplished before the effective date of this AD,
per the service bulletins listed in Table 6 of this AD, are
considered acceptable for compliance with the corresponding action
specified in this AD.
[[Page 33999]]
Table 6.--Previous Issues of Service Bulletins
------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
------------------------------------------------------------------------
A300-57-0235................ \*\ 02 September 27, 1999.
03 September 5, 2002.
A300-57-6088................ 02 September 5, 2000.
03 March 13, 2003.
------------------------------------------------------------------------
* Including Appendix 01.
Reporting
(o)(1) Although Airbus Service Bulletins A300-57A0234, A300-57-
0235, A300-57A6087, A300-57-6088, A300-57A0246, and A300-57A6101,
specify to submit certain information to the manufacturer, this AD
does not include such a requirement, except as provided by paragraph
(o)(2) of this AD.
(2) Where Airbus Service Bulletins A300-57A0246 and A300-57A6101
specify to submit a report of positive and negative findings of the
post-modification inspection required by paragraph (m) of this AD,
within 30 days after the effective date of this AD, submit a report
only of the positive findings of post-modification inspections to
Airbus, Customer Service Directorate, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France. The report must include the inspection
results, a description of any discrepancies found, the airplane
serial number, and the number of landings and flight hours on the
airplane. Under the provisions of the Paperwork Reduction Act of
1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget
(OMB) has approved the information collection requirements contained
in this AD and has assigned OMB Control Number 2120-0056.
Alternative Methods of Compliance (AMOCs)
(p)(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 per AD 2000-05-07 are approved as
AMOCs with this AD.
Related Information
(q) French airworthiness directives 2003-318(B), dated August
20, 2003; and F-2005-113 R1, dated July 20, 2005; also address the
subject of this AD.
Material Incorporated by Reference
(r) You must use the service information listed in Table 7 of
this AD to perform the actions that are required by this AD, unless
the AD specifies otherwise.
Table 7.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-57A0234............................. 02.......................... June 24, 1999.
A300-57A0234............................. * 03......................... September 2, 1999.
A300-57A0234............................. * 04......................... May 19, 2000.
A300-57A0234............................. * 05......................... February 19, 2002.
A300-57A0246............................. Original *................... May 20, 2005.
A300-57A6087............................. * 02......................... June 24, 1999.
A300-57A6087............................. * 03......................... May 19, 2000.
A300-57A6087............................. * 04......................... February 19, 2002.
A300-57A6101............................. Original *................... May 20, 2005.
A300-57-0234............................. 01.......................... March 11, 1998.
A300-57-0235............................. * 01......................... February 1, 1999.
A300-57-0235............................. 03.......................... September 5, 2002.
A300-57-0235............................. 04.......................... March 13, 2003.
A300-57-0235............................. 05.......................... December 3, 2003.
A300-57-6087............................. 01.......................... March 11, 1998.
A300-57-6088............................. * 01......................... February 1, 1999.
A300-57-6088............................. 02.......................... September 5, 2002.
A300-57-6088............................. 04.......................... December 3, 2003.
----------------------------------------------------------------------------------------------------------------
* Including Appendix 01.
(1) The Director of the Federal Register approved the
incorporation by reference of the documents listed in Table 8 of
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Table 8.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-57A0234............................. * 04......................... May 19, 2000.
A300-57A0234............................. * 05......................... February 19, 2002.
A300-57A0246............................. Original *................... May 20, 2005.
A300-57A6087............................. * 03......................... May 19, 2000.
A300-57A6087............................. * 04......................... February 19, 2002.
A300-57A6101............................. Original *................... May 20, 2005.
A300-57-0235............................. 03.......................... September 5, 2002.
A300-57-0235............................. 04.......................... March 13, 2003.
[[Page 34000]]
A300-57-0235............................. 05.......................... December 3, 2003.
A300-57-6088............................. 02.......................... September 5, 2002.
A300-57-6088............................. 04.......................... December 3, 2003.
----------------------------------------------------------------------------------------------------------------
* Including Appendix 01.
(2) On April 12, 2000 (65 FR 12077, March 8, 2000), the Director
of the Federal Register approved the incorporation by reference of
the documents listed in Table 9 of this AD.
Table 9.--Material Previously Incorporated by Reference
------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
------------------------------------------------------------------------
A300-57A0234................ 02 June 24, 1999.
A300-57A0234................ * 03 September 2, 1999.
A300-57A6087................ * 02 June 24, 1999.
------------------------------------------------------------------------
* Including Appendix 01.
(3) On October 20, 1999 (64 FR 49966, September 15, 1999), the
Director of the Federal Register approved the incorporation by
reference of the documents listed in Table 10 of this AD.
Table 10.--Material Previously Incorporated by Reference
------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
------------------------------------------------------------------------
A300-57-0234................ 01 March 11, 1998.
A300-57-0235................ * 01 February 1, 1999.
A300-57-6087................ 01 March 11, 1998.
A300-57-6088................ * 01 February 1, 1999.
------------------------------------------------------------------------
* Including Appendix 01.
(4) 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/
code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on May 31, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5244 Filed 6-12-06; 8:45 am]
BILLING CODE 4910-13-P
