Airworthiness Directives; Airbus Model A300 B4-600 and A300 B4-600R Series Airplanes; and A300 F4-605R and A300 C4-605R Variant F Airplanes, 69056-69059 [05-22216]
Download as PDF
<![CDATA[
69056
Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22110; Directorate
Identifier 2004–NM–205–AD; Amendment
39–14366; AD 2005–23–08]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B4–600 and A300 B4–600R Series
Airplanes; and A300 F4–605R and
A300 C4–605R Variant F 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
B4–600 and A300 B4–600R series
airplanes, and all Model A300 F4–605R
airplanes. That AD currently requires
repetitive inspections to detect cracks of
certain attachment holes, installation of
new fasteners, follow-on inspections or
repair if necessary, and modification of
the angle fittings of fuselage frame FR47.
This new AD revises certain inspection
thresholds and intervals. This new AD
also adds inspections to detect cracks of
additional attachment holes. This AD
results from reports of cracks found
before the inspection thresholds in the
existing AD and cracks found in nearby
areas not inspected by the existing AD.
We are issuing this AD to prevent
fatigue cracking of the forward fitting of
fuselage frame FR47, which could result
in reduced structural integrity of the
frame.
This AD becomes effective
December 19, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 19, 2005.
On July 8, 2002 (67 FR 38193, June 3,
2002), the Director of the Federal
Register approved the incorporation by
reference of Airbus Service Bulletin
A300–57–6086, dated June 6, 2000.
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,
DATES:
VerDate Aug<31>2005
15:39 Nov 10, 2005
Jkt 208001
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: 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.
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 2002–11–04, amendment
39–12765 (67 FR 38193, June 3, 2002).
The existing AD applies to all Airbus
Model A300 B4–600 and A300 B4–600R
series airplanes, and all Model A300
F4–605R airplanes. That NPRM was
published in the Federal Register on
August 16, 2005 (70 FR 48085). That
NPRM proposed to continue to require
repetitive inspections to detect cracks of
certain attachment holes, installation of
new fasteners, follow-on inspections or
repair if necessary, and modification of
the angle fittings of fuselage frame FR47.
That NPRM also proposed to revise
certain inspection thresholds and
intervals and add inspections to detect
cracks of additional attachment holes.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment that has been
received on the NPRM.
Request To Clarify Inspection in
Paragraph (k)
One commenter, the manufacturer,
requests that we clarify the inspection
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
specified in paragraph (k) of the NPRM.
The commenter states that the
inspection of hole T is not required if
‘‘any cracking is found’’ but is required
only if cracking is found at hole G.
We agree with the commenter that the
inspection of hole T is required only if
cracking is found at hole G. As specified
in the Accomplishment Instructions of
Airbus Service Bulletin A300–57–6086,
Revision 01, dated April 2, 2002 (which
is referenced as the appropriate source
of service information for accomplishing
the required actions for certain
airplanes), the inspection of hole T is
applicable only if cracking is found at
hole G. For clarity, we have revised
paragraph (k) of the final rule.
Clarification of Service Bulletin
References
We have revised certain references to
the service bulletins for clarity. We have
clarified that the actions specified in
paragraphs (j) and (k) of the final rule
are done in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6086,
Revision 01, dated April 2, 2002. We
have also clarified that the
modifications specified in paragraph (l)
of the final rule are done in accordance
with the Accomplishment Instructions
of Airbus Service Bulletin A300–57–
6050, Revision 03, dated May 31, 2001.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We have carefully reviewed the
available data, including the comment
that has been 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. This AD will
affect about 74 airplanes of U.S. registry.
E:\FR\FM\14NOR1.SGM
14NOR1
Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations
69057
ESTIMATED COSTS
Action
Work hours
Inspection per Airbus Service
Bulletin A300–57–6049.
Inspection per Airbus Service
Bulletin A300–57–6086.
Modification per Airbus Service Bulletin A300–57–6050.
Average
labor rate
per hour
Parts
Cost per airplane
Fleet cost
13
$65
$0
$845 ........................................
$62,530, per inspection cycle.
30
65
6,637–19,091
65–365
65
3,370
$8,587–$21,041, per inspection cycle.
$7,595–$27,095 ......................
$635,438–$1,557,034, per inspection cycle.
$562,030–$2,005,030.
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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.
VerDate Aug<31>2005
15:39 Nov 10, 2005
Jkt 208001
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 39–12765 (67
FR 38193, June 3, 2002) and by adding
the following new airworthiness
directive (AD):
I
2005–23–08 Airbus: Amendment 39–14366.
Docket No. FAA–2005–22110;
Directorate Identifier 2004–NM–205–AD.
Effective Date
(a) This AD becomes effective December
19, 2005.
Affected ADs
(b) This AD supersedes AD 2002–11–04.
Applicability
(c) This AD applies to Airbus Model A300
B4–601, B4–603, B4–620, and B4–622
airplanes; Model A300 B4–605R and B4–
622R airplanes; Model A300 F4–605R
airplanes; and Model A300 C4–605R Variant
F airplanes; certificated in any category;
except airplanes on which Airbus
Modification 12171 or 12249 has been
accomplished or on which Airbus Service
Bulletin A300–57–6069 has been
accomplished.
Unsafe Condition
(d) This AD was prompted by reports of
cracks found before the inspection thresholds
in the existing AD and cracks found in
nearby areas not inspected by the existing
AD. We are issuing this AD to prevent fatigue
cracking of the forward fitting of fuselage
frame FR47, which could result in reduced
structural integrity of the frame.
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
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.
Inspections for Attachment Holes on the
Internal Angles of the Wing Center Box, and
Corrective Action
(f) Perform a rotating probe inspection to
detect cracking of the applicable attachment
holes on the left and right internal angles of
the wing center box in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6049, Revision 06,
dated July 15, 2004. Do the inspection at the
applicable time specified by paragraph
1.E.(2), Accomplishment Timescale, of
Revision 06 of the service bulletin, except as
required by paragraph (m) of this AD. Repeat
the rotating probe inspection specified in this
paragraph thereafter at intervals not to
exceed the applicable interval specified in
Revision 06 of the service bulletin, except
that all touch-and-go landings must be
counted in determining the total number of
flight cycles between consecutive
inspections.
(g) If no cracking is found during any
inspection required by paragraph (f) of this
AD: Prior to further flight, install new
fasteners in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6049, Revision 06,
dated July 15, 2004.
(h) If any cracking is found during any
inspection required by paragraph (f) of this
AD: Prior to further flight, perform applicable
corrective actions (including reaming,
drilling, drill-stopping holes, chamfering,
performing follow-on inspections, and
installing new or oversize fasteners) in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6049, Revision 06, dated July 15, 2004,
except as required by paragraph (n) of this
AD.
Inspections for Attachment Holes in the
Horizontal Flange of the Internal Corner
Angle Fitting of Fuselage Frame FR47, and
Corrective Action
(i) Perform a rotating probe inspection to
detect cracking of the applicable attachment
holes in the horizontal flange of the internal
corner angle fitting of fuselage frame FR47,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6086, Revision 01, dated April 2, 2002.
Do the inspection at the applicable time
specified in paragraph 1.E., Compliance, of
Airbus Service Bulletin A300–57–6086,
E:\FR\FM\14NOR1.SGM
14NOR1
69058
Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations
Revision 01, dated April 2, 2002, except as
provided by paragraph (m) of this AD; or
within 1,500 flight cycles after July 8, 2002
(the effective date of AD 2002–11–04,
amendment 39–12765); whichever occurs
later. Repeat the rotating probe inspection
specified in this paragraph thereafter at
intervals not to exceed the applicable interval
specified in Airbus Service Bulletin A300–
57–6086, dated June 6, 2000, except that all
touch-and-go landings must be counted in
determining the total number of flight cycles
between consecutive inspections.
(j) If no cracking is found during any
inspection required by paragraph (i) of this
AD: Prior to further flight, install new
fasteners in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6086, Revision 01,
dated April 2, 2002.
(k) If any cracking is found during any
inspection required by paragraph (i) of this
AD: Prior to further flight, perform applicable
corrective actions (including inspecting hole
T if any cracking is found at hole G, reaming
the holes, and installing oversize fasteners) in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6086, Revision 01, dated April 2, 2002,
except as required by paragraph (n) of this
AD.
Modification of Angle Fittings of the Wing
Center Box
(l) Modify the left and right internal angle
fittings of the wing center box. The
modification includes performing a rotating
probe inspection to detect cracking, repairing
cracks, cold expanding holes, and installing
medium interference fitting bolts. Perform
the modification in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6050, Revision 03,
dated May 31, 2001; and at the applicable
time specified by paragraph 1.B.(4),
Accomplishment Timescale, of Airbus
Service Bulletin A300–57–6050, Revision 03,
dated May 31, 2001; except as required by
paragraphs (m) and (n) of this AD.
Exceptions to Specifications in Service
Bulletins
(m) Where the service bulletins specified
in paragraphs (f), (i), and (l) of this AD
specify a grace period relative to receipt of
the service bulletin, this AD requires
compliance within the applicable grace
period following the effective date of this AD,
if the threshold has been exceeded.
(n) If any crack is detected during any
inspection required by this AD, and the
applicable service bulletin specifies to
contact the manufacturer for disposition of
certain corrective actions: Prior to further
flight, repair in accordance with a method
approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the Direction
´ ´
Generale de l’Aviation Civile (DGAC) (or its
delegated agent).
Actions Accomplished According to
Previous Issue of Service Bulletins
(o) Actions accomplished prior to the
effective date of this AD in accordance with
Airbus Service Bulletin A300–57–6086,
dated June 6, 2000, are acceptable for
compliance with the requirements of
paragraph (i) of this AD.
(p) Modifications accomplished prior to
the effective date of this AD in accordance
with Airbus Service Bulletin A300–57–6050,
Revision 02, dated February 10, 2000; are
acceptable for compliance with the
requirements of paragraph (l) of this AD.
No Reporting Requirement
(q) Although Airbus Service Bulletin
A300–57–6049, Revision 06, dated July 15,
2004; and Airbus Service Bulletin A300–57–
6086, Revision 01, dated April 2, 2002;
specify to submit certain information to the
manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance
(AMOCs)
(r)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with 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 according
to AD 2002–11–04, are not approved as
AMOCs with this AD.
that are required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
the service bulletins listed in Table 2 of this
AD in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
(2) On July 8, 2002 (67 FR 38193, June 3,
2002), the Director of the Federal Register
approved the incorporation by reference of
Airbus Service Bulletin A300–57–6086,
dated June 6, 2000.
(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/
code_of_federal_regulations/
ibr_locations.html.
TABLE 1.—ALL MATERIAL
INCORPORATED BY REFERENCE
Airbus service
bulletin
Revision
level
Date
A300–57–6049,
excluding Appendix 01.
A300–57–6050
A300–57–6086
A300–57–6086
06 ............
July 15, 2004.
03 ............
Original ....
01 ............
May 31, 2001.
June 6, 2000.
April 2, 2002.
TABLE 2.—NEW MATERIAL
INCORPORATED BY REFERENCE
Airbus service
bulletin
Revision
level
Date
A300–57–6049,
excluding Appendix 01.
A300–57–6050
A300–57–6086
06 ............
July 15, 2004.
Related Information
(s) French airworthiness directive F–2004–
159, dated September 29, 2004, also
addresses the subject of this AD.
03 ............
01 ............
May 31, 2001.
April 2, 2002.
Material Incorporated by Reference
(t) You must use the service bulletins listed
in Table 1 of this AD to perform the actions
Airbus Service Bulletin A300–57–6050,
Revision 03, dated May 31, 2001, contains
the following effective pages:
Page number
Revision
level
shown on
page
Date shown on
page
1, 4, 10A–11, 75–76 ..............................................................................................................................................
2, 8–9, 17–32, 41–42, 57–58, 61–63, 77 .............................................................................................................
3, 5–7, 10, 12, 33–34, 37–38, 47, 59–60 .............................................................................................................
13–16, 35–36, 39–40, 43–46, 48–56, 64–74 ........................................................................................................
03 ............
02 ............
01 ............
Original ....
May 31, 2001.
February 10, 2000.
May 31, 1999.
September 9, 1994.
VerDate Aug<31>2005
15:39 Nov 10, 2005
Jkt 208001
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
E:\FR\FM\14NOR1.SGM
14NOR1
Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations
Issued in Renton, Washington, on October
31, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–22216 Filed 11–10–05; 8:45 am]
Certification Office, ASW–190, FAA,
Rotorcraft Directorate, 2601 Meacham
Boulevard, Fort Worth, Texas 76137–
4298; telephone (817) 222–5138; fax
(817) 222–5785.
SUPPLEMENTARY INFORMATION:
BILLING CODE 4910–13–P
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.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20947; Directorate
Identifier 2004–NM–245–AD; Amendment
39–14364; AD 2005–23–06]
RIN 2120–AA64
Airworthiness Directives; Learjet
Model 23, 24, 24A, 24B, 24B–A, 24D,
24D–A, 24E, 24F, 25, 25A, 25B, 25C,
25D, and 25F Airplanes Modified by
Supplemental Type Certificate
SA1731SW, SA1669SW, or SA1670SW
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Learjet Model 23, 24, 24A, 24B, 24B–A,
24D, 24D–A, 24E, 24F, 25, 25A, 25B,
25C, 25D, and 25F airplanes. This AD
requires removing the thrust reverser
accumulator, and making the thrust
reverser hydraulic system and the thrust
reversers inoperable. This AD results
from reports of the failure of two thrust
reverser accumulators. We are issuing
this AD to prevent failure of the thrust
reverser accumulators, due to fatigue
cracking on the female threads, which
could result in the loss of hydraulic
power and damage to the surrounding
airplane structure.
DATES: This AD becomes effective
December 19, 2005.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of December 19, 2005.
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 The Nordam Group, Nacelle/
Thrust Reverser Systems Division, 6911
North Whirlpool Drive, Tulsa,
Oklahoma 74117, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Jim
Rankin, Aerospace Engineer, Special
VerDate Aug<31>2005
15:39 Nov 10, 2005
Jkt 208001
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Learjet Model 23, 24,
24A, 24B, 24B–A, 24D, 24D–A, 24E,
24F, 25, 25A, 25B, 25C, 25D, and 25F
airplanes. That NPRM was published in
the Federal Register on April 14, 2005
(70 FR 19718). That NPRM proposed to
require removing the thrust reverser
accumulator, and making the thrust
reverser hydraulic system and the thrust
reversers inoperable.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Withdraw NPRM
One commenter does not support the
NPRM. The commenter asserts that
deactivating the thrust reversers will
cause more accidents, especially under
wet or winter runway conditions. The
commenter also asserts that one in-flight
failure of a thrust reverser does not
justify the NPRM given the countless
safe operations without thrust reverser
failures. The commenter states that
‘‘[the FAA] also [has] not looked or
measured the increase of accidents that
will be caused by this [NPRM].’’ As
further justification for not supporting
the NPRM, the commenter states that
the NPRM does not account for the cost
of brake and tire wear that would be
incurred if the thrust reversers are
deactivated. We infer that the
commenter would like us to withdraw
the NPRM.
We do not agree, since we have
determined that an unsafe condition
exists, and that the interim actions of
this AD are necessary to ensure the
continued safety of the affected fleet.
The one thrust reverser failure on a
Learjet Model 25B airplane that
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
69059
occurred in flight led to an emergency
landing. A second failure occurred
during proof testing and resulted in
injury to a person. We acknowledge the
commenter’s concern with deactivating
the thrust reversers; however, the
affected Model 23, 24, 24A, 24B, 24B–
A, 24D, 24D–A, 24E, 24F, 25, 25A, 25B,
25C, 25D, and 25F airplanes were not
originally type certificated with thrust
reversers installed. Furthermore, we
estimate that half of these Learjet model
airplanes in service today are operating
without thrust reversers. Therefore, an
increase in accidents due to
deactivation of the affected thrust
reversers is unlikely.
Regarding the cost impact of this AD,
we point out that the economic analysis
of the AD is limited only to the cost of
actions actually required by the AD; it
does not include incidental costs. In any
case, we have determined that direct
and incidental costs are outweighed by
the safety benefits of this AD. Therefore,
no change to this AD is necessary in this
regard.
Request To Revise Requirements of
NPRM
Two commenters request that we
revise the NPRM to require repetitive
nondestructive testing or x-ray
inspections of the thrust reverser
accumulator, instead of proposing to
deactivate the thrust reversers. One of
the commenters states that inspection of
the suspected point of failure (the
female threads of the accumulator)
would be sufficient to prevent failure of
the thrust reverser accumulator. The
commenter suggests that deactivation of
the thrust reversers could be required if
damage is found during an inspection.
We do not agree, since the
commenters provide no technical
justification for revising the
requirements of this AD. The history of
crack growth on the affected thrust
reversers is unknown. In addition, there
have been no studies done to determine
an appropriate inspection interval for
providing an acceptable level of safety.
As stated in the NPRM, the parts
manufacturer currently is developing a
modification that will address the
unsafe condition of this AD. Once this
modification is developed, approved,
and available, we may consider
additional rulemaking. Therefore no
change to this AD is necessary in this
regard.
Request To Expand Applicability
One commenter, the parts
manufacturer, requests that we delete
reference to Supplemental Type
Certificates (STCs) SA1731SW,
SA1669SW, and SA1670SW from the
E:\FR\FM\14NOR1.SGM
14NOR1
]]>Agencies
[Federal Register Volume 70, Number 218 (Monday, November 14, 2005)]
[Rules and Regulations]
[Pages 69056-69059]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-22216]
[[Page 69056]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22110; Directorate Identifier 2004-NM-205-AD;
Amendment 39-14366; AD 2005-23-08]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600 and A300 B4-
600R Series Airplanes; and A300 F4-605R and A300 C4-605R Variant F
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 B4-600 and A300 B4-600R
series airplanes, and all Model A300 F4-605R airplanes. That AD
currently requires repetitive inspections to detect cracks of certain
attachment holes, installation of new fasteners, follow-on inspections
or repair if necessary, and modification of the angle fittings of
fuselage frame FR47. This new AD revises certain inspection thresholds
and intervals. This new AD also adds inspections to detect cracks of
additional attachment holes. This AD results from reports of cracks
found before the inspection thresholds in the existing AD and cracks
found in nearby areas not inspected by the existing AD. We are issuing
this AD to prevent fatigue cracking of the forward fitting of fuselage
frame FR47, which could result in reduced structural integrity of the
frame.
DATES: This AD becomes effective December 19, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 19,
2005.
On July 8, 2002 (67 FR 38193, June 3, 2002), the Director of the
Federal Register approved the incorporation by reference of Airbus
Service Bulletin A300-57-6086, dated June 6, 2000.
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: 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.
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 2002-11-04, amendment
39-12765 (67 FR 38193, June 3, 2002). The existing AD applies to all
Airbus Model A300 B4-600 and A300 B4-600R series airplanes, and all
Model A300 F4-605R airplanes. That NPRM was published in the Federal
Register on August 16, 2005 (70 FR 48085). That NPRM proposed to
continue to require repetitive inspections to detect cracks of certain
attachment holes, installation of new fasteners, follow-on inspections
or repair if necessary, and modification of the angle fittings of
fuselage frame FR47. That NPRM also proposed to revise certain
inspection thresholds and intervals and add inspections to detect
cracks of additional attachment holes.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that has been
received on the NPRM.
Request To Clarify Inspection in Paragraph (k)
One commenter, the manufacturer, requests that we clarify the
inspection specified in paragraph (k) of the NPRM. The commenter states
that the inspection of hole T is not required if ``any cracking is
found'' but is required only if cracking is found at hole G.
We agree with the commenter that the inspection of hole T is
required only if cracking is found at hole G. As specified in the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6086,
Revision 01, dated April 2, 2002 (which is referenced as the
appropriate source of service information for accomplishing the
required actions for certain airplanes), the inspection of hole T is
applicable only if cracking is found at hole G. For clarity, we have
revised paragraph (k) of the final rule.
Clarification of Service Bulletin References
We have revised certain references to the service bulletins for
clarity. We have clarified that the actions specified in paragraphs (j)
and (k) of the final rule are done in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6086,
Revision 01, dated April 2, 2002. We have also clarified that the
modifications specified in paragraph (l) of the final rule are done in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6050, Revision 03, dated May 31, 2001.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
We have carefully reviewed the available data, including the
comment that has been 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. This AD will affect about 74 airplanes of U.S.
registry.
[[Page 69057]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average
Action Work hours labor rate Parts Cost per airplane Fleet cost
per hour
----------------------------------------------------------------------------------------------------------------
Inspection per Airbus Service 13 $65 $0 $845............. $62,530, per
Bulletin A300-57-6049. inspection
cycle.
Inspection per Airbus Service 30 65 6,637-19,091 $8,587-$21,041, $635,438-$1,557,0
Bulletin A300-57-6086. per inspection 34, per
cycle. inspection
cycle.
Modification per Airbus Service 65-365 65 3,370 $7,595-$27,095... $562,030-$2,005,0
Bulletin A300-57-6050. 30.
----------------------------------------------------------------------------------------------------------------
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 39-12765 (67 FR 38193, June 3, 2002) and by adding
the following new airworthiness directive (AD):
2005-23-08 Airbus: Amendment 39-14366. Docket No. FAA-2005-22110;
Directorate Identifier 2004-NM-205-AD.
Effective Date
(a) This AD becomes effective December 19, 2005.
Affected ADs
(b) This AD supersedes AD 2002-11-04.
Applicability
(c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620,
and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes;
Model A300 F4-605R airplanes; and Model A300 C4-605R Variant F
airplanes; certificated in any category; except airplanes on which
Airbus Modification 12171 or 12249 has been accomplished or on which
Airbus Service Bulletin A300-57-6069 has been accomplished.
Unsafe Condition
(d) This AD was prompted by reports of cracks found before the
inspection thresholds in the existing AD and cracks found in nearby
areas not inspected by the existing AD. We are issuing this AD to
prevent fatigue cracking of the forward fitting of fuselage frame
FR47, which could result in reduced structural integrity of the
frame.
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.
Inspections for Attachment Holes on the Internal Angles of the Wing
Center Box, and Corrective Action
(f) Perform a rotating probe inspection to detect cracking of
the applicable attachment holes on the left and right internal
angles of the wing center box in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6049, Revision 06,
dated July 15, 2004. Do the inspection at the applicable time
specified by paragraph 1.E.(2), Accomplishment Timescale, of
Revision 06 of the service bulletin, except as required by paragraph
(m) of this AD. Repeat the rotating probe inspection specified in
this paragraph thereafter at intervals not to exceed the applicable
interval specified in Revision 06 of the service bulletin, except
that all touch-and-go landings must be counted in determining the
total number of flight cycles between consecutive inspections.
(g) If no cracking is found during any inspection required by
paragraph (f) of this AD: Prior to further flight, install new
fasteners in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15,
2004.
(h) If any cracking is found during any inspection required by
paragraph (f) of this AD: Prior to further flight, perform
applicable corrective actions (including reaming, drilling, drill-
stopping holes, chamfering, performing follow-on inspections, and
installing new or oversize fasteners) in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6049,
Revision 06, dated July 15, 2004, except as required by paragraph
(n) of this AD.
Inspections for Attachment Holes in the Horizontal Flange of the
Internal Corner Angle Fitting of Fuselage Frame FR47, and Corrective
Action
(i) Perform a rotating probe inspection to detect cracking of
the applicable attachment holes in the horizontal flange of the
internal corner angle fitting of fuselage frame FR47, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A300-57-6086, Revision 01, dated April 2, 2002. Do the inspection at
the applicable time specified in paragraph 1.E., Compliance, of
Airbus Service Bulletin A300-57-6086,
[[Page 69058]]
Revision 01, dated April 2, 2002, except as provided by paragraph
(m) of this AD; or within 1,500 flight cycles after July 8, 2002
(the effective date of AD 2002-11-04, amendment 39-12765); whichever
occurs later. Repeat the rotating probe inspection specified in this
paragraph thereafter at intervals not to exceed the applicable
interval specified in Airbus Service Bulletin A300-57-6086, dated
June 6, 2000, except that all touch-and-go landings must be counted
in determining the total number of flight cycles between consecutive
inspections.
(j) If no cracking is found during any inspection required by
paragraph (i) of this AD: Prior to further flight, install new
fasteners in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2,
2002.
(k) If any cracking is found during any inspection required by
paragraph (i) of this AD: Prior to further flight, perform
applicable corrective actions (including inspecting hole T if any
cracking is found at hole G, reaming the holes, and installing
oversize fasteners) in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6086, Revision 01,
dated April 2, 2002, except as required by paragraph (n) of this AD.
Modification of Angle Fittings of the Wing Center Box
(l) Modify the left and right internal angle fittings of the
wing center box. The modification includes performing a rotating
probe inspection to detect cracking, repairing cracks, cold
expanding holes, and installing medium interference fitting bolts.
Perform the modification in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6050, Revision 03,
dated May 31, 2001; and at the applicable time specified by
paragraph 1.B.(4), Accomplishment Timescale, of Airbus Service
Bulletin A300-57-6050, Revision 03, dated May 31, 2001; except as
required by paragraphs (m) and (n) of this AD.
Exceptions to Specifications in Service Bulletins
(m) Where the service bulletins specified in paragraphs (f),
(i), and (l) of this AD specify a grace period relative to receipt
of the service bulletin, this AD requires compliance within the
applicable grace period following the effective date of this AD, if
the threshold has been exceeded.
(n) If any crack is detected during any inspection required by
this AD, and the applicable service bulletin specifies to contact
the manufacturer for disposition of certain corrective actions:
Prior to further flight, repair in accordance with a method approved
by either the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the Direction G[eacute]n[eacute]rale
de l'Aviation Civile (DGAC) (or its delegated agent).
Actions Accomplished According to Previous Issue of Service Bulletins
(o) Actions accomplished prior to the effective date of this AD
in accordance with Airbus Service Bulletin A300-57-6086, dated June
6, 2000, are acceptable for compliance with the requirements of
paragraph (i) of this AD.
(p) Modifications accomplished prior to the effective date of
this AD in accordance with Airbus Service Bulletin A300-57-6050,
Revision 02, dated February 10, 2000; are acceptable for compliance
with the requirements of paragraph (l) of this AD.
No Reporting Requirement
(q) Although Airbus Service Bulletin A300-57-6049, Revision 06,
dated July 15, 2004; and Airbus Service Bulletin A300-57-6086,
Revision 01, dated April 2, 2002; specify to submit certain
information to the manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance (AMOCs)
(r)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with 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 according to AD 2002-11-04, are
not approved as AMOCs with this AD.
Related Information
(s) French airworthiness directive F-2004-159, dated September
29, 2004, also addresses the subject of this AD.
Material Incorporated by Reference
(t) You must use the service bulletins listed in Table 1 of this
AD to perform the actions that are required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of the service bulletins listed in Table
2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On July 8, 2002 (67 FR 38193, June 3, 2002), the Director of
the Federal Register approved the incorporation by reference of
Airbus Service Bulletin A300-57-6086, dated June 6, 2000.
(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/code_of_federal_regulations/ibr_locations.html.
Table 1.--All Material Incorporated by Reference
------------------------------------------------------------------------
Airbus service bulletin Revision level Date
------------------------------------------------------------------------
A300-57-6049, excluding Appendix 06.............. July 15, 2004.
01.
A300-57-6050.................... 03.............. May 31, 2001.
A300-57-6086.................... Original........ June 6, 2000.
A300-57-6086.................... 01.............. April 2, 2002.
------------------------------------------------------------------------
Table 2.--New Material Incorporated by Reference
------------------------------------------------------------------------
Airbus service bulletin Revision level Date
------------------------------------------------------------------------
A300-57-6049, excluding Appendix 06.............. July 15, 2004.
01.
A300-57-6050.................... 03.............. May 31, 2001.
A300-57-6086.................... 01.............. April 2, 2002.
------------------------------------------------------------------------
Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31,
2001, contains the following effective pages:
------------------------------------------------------------------------
Revision level
Page number shown on page Date shown on page
------------------------------------------------------------------------
1, 4, 10A-11, 75-76.......... 03............ May 31, 2001.
2, 8-9, 17-32, 41-42, 57-58, 02............ February 10, 2000.
61-63, 77.
3, 5-7, 10, 12, 33-34, 37-38, 01............ May 31, 1999.
47, 59-60.
13-16, 35-36, 39-40, 43-46, Original...... September 9, 1994.
48-56, 64-74.
------------------------------------------------------------------------
[[Page 69059]]
Issued in Renton, Washington, on October 31, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-22216 Filed 11-10-05; 8:45 am]
BILLING CODE 4910-13-P
