Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310 Series Airplanes, 62890-62895 [E6-17661]
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<![CDATA[
62890
Federal Register / Vol. 71, No. 208 / Friday, October 27, 2006 / Rules and Regulations
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 39–14194 (70
FR 42267, July 22, 2005) and by adding
the following new airworthiness
directive (AD):
I
2006–22–02 Airbus: Amendment 39–14799.
Docket No. FAA–2006–25088;
Directorate Identifier 2006–NM–085–AD.
Effective Date
(a) This AD becomes effective December 1,
2006.
Affected ADs
(b) This AD supersedes AD 2005–15–05.
Applicability
(c) This AD applies to Airbus Model A300
B4–601, B4–603, B4–620, B4–622, B4–605R,
B4–622R, F4–605R, F4–622R, and C4–605R
Variant F airplanes; certificated in any
category; equipped with a Hamilton
Sundstrand Ram Air Turbine (RAT).
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(d) This AD results from reports of holes
in the ram air turbine (RAT) hub cover. We
are issuing this AD to prevent a hole in the
RAT hub cover. A hole in the RAT hub cover
could allow water to enter the RAT governing
mechanism, freeze during flight, and jam the
governing mechanism. In addition, the metal
particles that result from chafing between the
hydraulic flexible hose and the RAT could
mix with the lubricant grease and degrade
the governing mechanism. In an emergency,
a jammed or degraded RAT could result in
its failure to deploy, loss of hydraulic
pressure or electrical power to the airplane,
and consequent reduced controllability 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.
14:48 Oct 26, 2006
Inspection and Related Investigative/
Corrective Actions
(f) At the applicable time specified in
paragraph (f)(1) or (f)(2) of this AD: Do a onetime detailed inspection for evidence of
chafing between the hydraulic flexible hose
and the RAT hub, and any applicable related
investigative and corrective actions, by
accomplishing all of the applicable actions
specified in the Accomplishment
Instructions of Airbus Service Bulletin A300–
29–6054, Revision 01, excluding Appendix
01, dated November 4, 2004; or Revision 02,
excluding Appendix 01, dated January 12,
2006. After the effective date of this AD, only
Revision 02 of the service bulletin may be
used. Any applicable corrective actions must
be accomplished before further flight. Where
the service bulletins specify to submit certain
information to the manufacturer, and to
submit damaged RATs to the vendor or a
repair station, this AD does not include those
requirements.
(1) For airplanes having serial numbers (S/
Ns) 0812, 0813, 0815 through 0818 inclusive,
0821 through 0828 inclusive, and 0836
through 0838 inclusive: Within 2,500 flight
hours after August 26, 2005 (the effective
date of AD 2005–15–05).
(2) For airplanes not identified in
paragraph (f)(1) of this AD: Within 2,500
flight hours after the effective date 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.’’
Related Information
(i) French airworthiness directive F–2006–
035, dated February 1, 2006, also addresses
the subject of this AD.
Material Incorporated by Reference
(j) You must use Airbus Service Bulletin
A300–29–6054, Revision 01, excluding
Appendix 01, dated November 4, 2004; or
Airbus Service Bulletin A300–29–6054,
Revision 02, excluding Appendix 01, dated
January 12, 2006; 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
Airbus Service Bulletin A300–29–6054,
Revision 02, excluding Appendix 01, dated
January 12, 2006, in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On August 26, 2005 (70 FR 42267, July
22, 2005), the Director of the Federal Register
approved the incorporation by reference of
Airbus Service Bulletin A300–29–6054,
Revision 01, excluding Appendix 01, dated
November 4, 2004.
(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.
Issued in Renton, Washington, on October
11, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–17657 Filed 10–26–06; 8:45 am]
BILLING CODE 4910–13–P
Actions Accomplished Previously
Unsafe Condition
VerDate Aug<31>2005
Restatement of the Requirements of AD
2005–15–05 With Compliance Times for New
Airplanes
Jkt 211001
(g) Actions accomplished before the
effective date of this AD, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A300–29–6054, excluding
Appendix 01, dated June 8, 2004, are
acceptable for compliance with the
corresponding actions specified in this AD.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) AMOCs approved previously in
accordance with AD 2005–15–05 are
approved as AMOCs for the corresponding
provisions of this AD.
PO 00000
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21343; Directorate
Identifier 2004–NM–117–AD; Amendment
39–14800; AD 2006–22–03]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B4–600, B4–600R, and F4–600R
Series Airplanes, and Model C4–605R
Variant F Airplanes (Collectively Called
A300–600 Series Airplanes); and Model
A310 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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Federal Register / Vol. 71, No. 208 / Friday, October 27, 2006 / Rules and Regulations
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus models, as specified above. This
AD requires modifying the aft pressure
bulkhead for improved corrosion
protection and drainage, and related
concurrent actions. This AD results
from severe corrosion found in the
lower rim area of the aft pressure
bulkhead during routine maintenance of
an airplane. We are issuing this AD to
prevent corrosion on the inner rim angle
and cleat profile splice of the aft
pressure bulkhead, which could result
in the loss of airplane structural
integrity.
DATES: This AD becomes effective
December 1, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 1, 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 Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
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Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Airbus Model A300 B4–
600, B4–600R, and F4–600R series
airplanes, and Model C4–605R Variant F
airplanes (collectively called A300–600
series airplanes); and Model A310 series
airplanes. That NPRM was published in
the Federal Register on June 3, 2005 (70
FR 32547). That NPRM proposed to
require modifying the aft pressure
VerDate Aug<31>2005
14:48 Oct 26, 2006
Jkt 211001
bulkhead for improved corrosion
protection and drainage, and related
concurrent actions.
Actions Since NPRM Was Issued
Since we issued the NPRM, Airbus
has released Service Bulletin A310–53–
2025, Revision 06, dated August 3,
2006. In the NPRM, we referred to
Airbus Service Bulletin A310–53–2025,
Revision 5, dated March 24, 1989, as the
appropriate source of service
information for modifying the aft
pressure bulkhead to improve the
fatigue life of the attachment angles at
frame (FR)80/82 on Model A310 series
airplanes. The procedures in Revision
06 are essentially the same as those in
Revision 5. Therefore, we have revised
Table 1 of this AD to refer to Revision
06 as the appropriate source of service
information for accomplishing the
modification on Model A310 series
airplanes. We have also added a new
paragraph (k) to this AD, which gives
credit for actions accomplished before
the effective date of this AD in
accordance with Revision 5.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Use Alternative Sealant
FedEx requests that we revise the
NPRM to identify an alternative to
sealant PR–2752 (consumable material
list (CML) 09–035), since it is not
available from any worldwide source.
FedEx states that Airbus has identified
an alternative sealant for use on FedEx’s
airplanes. However, that sealant has an
1,800-flight-cycle life limit, which
creates an undue burden on FedEx’s
operational planning of airplane
downtime and resources. FedEx also
states that the FAA issued alternative
method of compliance (AMOC) letter
ANM–116–04–175, dated May 27, 2004,
allowing use of that same alternative
sealant, which requires repetitively
resealing the applicable areas within
intervals of 1,800 flight cycles. FedEx
asserts that sealant PR–2752, due to its
brittleness and low elongation
properties, tends to separate from the
structure, creating a moisture trap that
leads to corrosion. FedEx proposes
substituting sealant PR–2752 with an
epoxy adhesive like 3M Scotch-Weld
EC–2216 to maintain an adequate level
of safety and meet design parameters.
We partially agree. Since we issued
the NPRM, Airbus has identified
another alternative to sealant PR–2752.
Sealant MC–650B (CML 09–056), from
Chemetall, should be available in
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Fmt 4700
Sfmt 4700
62891
December of 2006. Airbus Service
Bulletin A310–53–2025, Revision 06,
which we described previously, already
specifies using MC–650B. Although
Airbus Service Bulletin A300–53–6006,
Revision 3, dated March 24, 1989,
specifies using sealant PR–2752, Airbus
does not intend to revise this service
bulletin because all affected Model
A300–600 series airplanes have been
modified already. Airbus has advised us
that it does intend to revise Airbus
Service Bulletins A300–53–6017 and
A310–53–2036, both Revision 02, both
dated February 25, 2004, to specify
using sealant MC–650B. We have
revised paragraph (g) of this AD to allow
use of sealant MC–650B as an
alternative to sealant PR–2752.
Request To Withdraw NPRM
FedEx requests that we withdraw the
NPRM. As justification, FedEx states
that, due to the complex structural
configuration of the aft pressure
bulkhead between FR80 and FR82 and
the use of several different compounds
for modification of the drain hole, the
referenced service bulletins in the
NPRM need to identify additional work
instructions and substitute materials. In
addition, FedEx asserts that removal of
sealants, especially sealant PR–2752,
could cause more surface protection
damage because of the complexity of the
joint. FedEx further requests that we
coordinate with the Direction Generale
de l’Aviation Civile (DGAC), which is
the airworthiness authority for France,
to ask Airbus to develop a better
solution for the application of corrosioninhibiting compounds and sealants in
the discrepant area.
We do not agree to withdraw the
NPRM. As stated previously, Airbus has
either revised or intends to revise the
referenced service bulletins to identify
an alternative sealant. Also, the revised
service bulletins use specific indicators
and criteria to avoid removing the
sealant if it is not necessary. These
changes should alleviate the complexity
of the service bulletins. We have not
changed this AD in this regard.
Request To Harmonize Various Service
Bulletins and ADs
FedEx requests that we harmonize the
modification and inspection programs
of several service bulletins and ADs that
address corrosion in the aft pressure
bulkhead. For Model A300–600 series
airplanes, FedEx cites Airbus Service
Bulletins A300–53–6006, Revision 3,
dated March 24, 1989; A300–53–6017,
Revision 02, dated February 25, 2004;
and A300–53–6136, dated October 27,
2004. For Model A310 series airplanes,
FedEx cites Airbus Service Bulletins
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Federal Register / Vol. 71, No. 208 / Friday, October 27, 2006 / Rules and Regulations
A310–53–2025, Revision 5, dated March
24, 1989; A310–53–2036, Revision 02,
dated February 25, 2004; and A310–53–
2114, dated October 27, 2004. FedEx
also cites AD 88–06–03, amendment 39–
5871 (53 FR 7730, March 10, 1988), and
AD 98–19–22, amendment 39–10763 (63
FR 49656, September 17, 1998).
We disagree and have not revised this
AD in this regard. Although the various
service bulletins and ADs involve work
in the area of the aft pressure bulkhead,
they address unsafe conditions related
to either corrosion or fatigue. Also, the
affected airplanes in the various service
bulletins and ADs are different. This AD
and AD 88–06–03 both refer to Airbus
Service Bulletin A310–53–2025 as the
appropriate source of service
information for modifying the
attachment of the rear pressure
bulkhead to FR80/82. This AD requires
Revision 06 of that service bulletin,
while AD 88–06–03 requires the original
issue, dated April 21, 1986, or Revision
3, dated April 7, 1987. However, we
AD—
specified in the NPRM that paragraph (i)
of this AD provides credit for
accomplishment of paragraph A.2. of
AD 88–06–03. AD 88–06–03 also refers
to Airbus Service Bulletin A310–53–
2024, Revision 1, dated June 20, 1986;
or Revision 3, dated February 17, 1987;
as appropriate sources of service
information for accomplishing repetitive
inspections of the rear pressure
bulkhead for cracks. We issued AD 88–
06–03 to improve the fatigue life of the
attachment angles at FR80/82 on certain
Model A310 series airplanes.
AD 98–19–22 refers to Airbus Service
Bulletins A300–53–6066 and A310–53–
2092, both dated October 16, 1996; and
Revision 01, both dated March 11, 1998;
as appropriate sources of service
information for accomplishing repetitive
inspections to detect corrosion of the
lower rim area of the aft pressure
bulkhead. After we issued AD 98–19–
22, severe corrosion was found on
certain airplanes that were inspected
previously in accordance with that AD.
Refers to airbus service bulletin—
88–06–03 ...............................................
98–19–22 (superseded by AD 2005–
26–16).
2005–26–16 ...........................................
A310–53–2024,
sion 3.
A310–53–2025,
vision 3.
A300–53–6066,
vision 01.
A310–53–2092,
vision 01.
A300–53–6136,
A300–53–6017,
A310–53–2036,
A300–53–6006,
A310–53–2025,
rmajette on PROD1PC67 with RULES1
Request for Credit for Airbus Service
Bulletins A300–53–6066 and A310–53–
2092
FedEx requests that we give credit for
accomplishment of Airbus Service
Bulletins A300–53–6066 and A310–53–
2092. FedEx states that these service
bulletins are referenced in AD 98–19–22
and also involve the lower rim area of
the pressure bulkhead.
We disagree. As discussed previously,
the repetitive inspections specified in
Airbus Service Bulletins A300–53–6066
and A310–53–2092 are obsolete and
inadequate for addressing corrosion at
the lower rim area of the rear pressure
bulkhead. Further, the referenced
service bulletins in this AD are intended
to not only improve the corrosion
protection at the lower rim area of the
aft pressure bulkhead, but to also
improve the fatigue life of the
VerDate Aug<31>2005
14:48 Oct 26, 2006
Jkt 211001
Requiring—
Repetitive inspections ...........................
Fatigue.
original issue and Re-
Modification ...........................................
Fatigue.
original issue and Re-
Repetitive inspections ...........................
Corrosion.
original issue and Re-
Repetitive inspections ...........................
Corrosion.
Revision 01 ................
Repetitive inspections with reduced intervals.
Repetitive inspections with reduced intervals.
Modification ...........................................
Modification ...........................................
Modification ...........................................
Modification ...........................................
Corrosion.
Revision
Revision
Revision
Revision
02 ................
02 ................
3 ..................
06 ................
attachment angles at FR80/82. We have
not changed this AD in this regard.
Request To Refer to Airbus Service
Bulletins A300–53–6136 and A310–53–
2114
FedEx requests that we revise Table 1
of the NPRM to refer to Airbus Service
Bulletins A300–53–6136 and A310–53–
2114, both dated October 27, 2004,
instead of Airbus Service Bulletins
A300–53–6006, Revision 3, dated March
24, 1989 (for Model A300–600 series
airplanes); and A310–53–2025, Revision
5, dated March 24, 1989 (for Model
A310 series airplanes). (In the NPRM,
we referred to Airbus Service Bulletins
A300–53–6006, Revision 3; and A310–
53–2025, Revision 5; as appropriate
sources of service information for
accomplishing certain related
concurrent actions.) As justification,
FedEx states that Airbus Service
PO 00000
Addressing—
Revision 1 and Revi-
A310–53–2114, Revision 01 ................
This AD ..................................................
Based on those findings, we determined
that the inspection methods in AD 98–
19–22 were obsolete and inadequate,
and that a new inspection program was
necessary. Subsequently, we issued AD
2005–26–16, amendment 39–14437 (70
FR 77307, December 30, 2005), to
supersede AD 98–19–22. The
inspections required by AD 98–19–22,
which refers to Airbus Service Bulletins
A300–53–6066 and A310–53–2092,
were not retained in AD 2005–26–16.
AD 2005–26–16 instead refers to Airbus
Service Bulletins A300–53–6136,
Revision 01, dated July 18, 2005; and
A310–53–2114, Revision 01, dated
September 1, 2005; as the appropriate
sources of service information for
accomplishing the actions in that AD.
Further, Airbus has informed us that it
issued Airbus Service Bulletins A300–
53–6136 and A310–53–2114 to
supersede Airbus Service Bulletins
A300–53–6066 and A310–53–2092. The
table below provides an overview of the
ADs we have issued.
Frm 00018
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Sfmt 4700
Corrosion.
Corrosion.
Corrosion.
Fatigue.
Fatigue.
Bulletins A300–53–6136 and A310–53–
2114 were issued to address incomplete
adhesion of sealant and damage caused
to surface protection during cleaning of
the drain hole, or during
accomplishment of Airbus Service
Bulletins A300–53–6006 and A310–53–
2025. FedEx states that Airbus Service
Bulletins A300–53–6136 and A310–53–
2114 also involve inspections for
corrosion in the lower rim angle area of
the rear pressure bulkhead. FedEx
further requests that we coordinate with
Airbus and the DGAC to address the
apparent discrepancy between Airbus
Service Bulletins A300–53–6136 and
A300–53–6006 and between Airbus
Service Bulletins and A310–53–2025
and A310–53–2114.
We do not agree to refer to Airbus
Service Bulletins A300–53–6136 and
A310–53–2114 in this AD. As stated
previously, AD 2005–26–16 mandates
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Federal Register / Vol. 71, No. 208 / Friday, October 27, 2006 / Rules and Regulations
accomplishment of Revision 01 of
Airbus Service Bulletins A300–53–6136
and A310–53–2114, as applicable.
Airbus has informed us that Airbus
Service Bulletins A300–53–6136 and
A310–53–2114 were issued to address
corrosion prevention, while Airbus
Service Bulletins A300–53–6006 and
A310–53–2025 were issued to address
an unsafe condition caused by fatigue.
Airbus has also informed us that Airbus
Service Bulletins A300–53–6136 and
A310–53–2114 mention
accomplishment of 6767yttyyAirbus
Service Bulletins A300–53–6006 and
A310–53–2025 only as possible sources
for corrosion if surface protection is
damaged. Airbus states that the service
bulletins must be accomplished
independently of each other. Therefore,
we have not changed this AD in this
regard.
Request for Credit for Airbus Service
Bulletin A300–53–0218
The Air Transport Association (ATA),
on behalf of its member ASTAR Air
Cargo (ASTAR), questions the basis of
the NPRM since Airbus has issued
Service Bulletin A300–53–0218,
Revision 02, dated May 10, 2005.
ASTAR states that it has accomplished
Revision 02 of the service bulletin and
intends to use it to show compliance
with the proposed requirements of the
NPRM. We infer that ASTAR would like
us to revise this AD to allow Airbus
Service Bulletin A300–53–0218,
Revision 02, as an acceptable method of
compliance.
We do not agree that Revision 02 of
Airbus Service Bulletin A300–53–0218
is acceptable for complying with the
requirements of this AD. For Model
A300–600 series airplanes, this AD
requires accomplishment of Airbus
Service Bulletins A300–53–6017,
Revision 02; and A300–53–6006,
Revision 3. Airbus Service Bulletin
A300–53–6017 describes procedures for
improving the corrosion protection at
the aft pressure bulkhead and enlarging
the drainholes for improved drainage.
Airbus Service Bulletin A300–53–6006
describes procedures for modifying the
aft pressure bulkhead to improve the
fatigue life of the attachment angles at
FR80/82. Airbus Service Bulletin A300–
53–0218 describes procedures for
inspecting for corrosion and cracks in
the upper rim area of the rear pressure
bulkhead aft face, between stringer
(STGR) 26 left-hand (LH) and right-hand
(RH) and all service apertures, and
removing corrosion and repairing as
necessary. The service bulletins address
different issues; therefore, we have not
changed this AD in this regard.
We point out that Airbus Service
Bulletin A300–53–218, Revision 1, July
28, 1989, is mandated by AD 90–03–08,
amendment 39–6481 (55 FR 1799,
January 19, 1990). That AD applies to all
Model A300 airplanes. That AD requires
repetitive inspections for cracking and
corrosion in the lower rim area of the
rear pressure bulkhead and adjacent
areas, repetitive inspections for cracking
or corrosion in the service apertures and
the upper rim area of the rear pressure
bulkhead, and corrective actions if
necessary. We issued AD 90–03–08 to
prevent reduced structural capability of
the fuselage and subsequent
decompression of the airplane. Since we
issued AD 90–03–08, we have issued an
62893
NPRM to supersede that AD. That
NPRM was published in the Federal
Register on August 1, 2006 (71 FR
43386). That NPRM refers to Revision
02 of Airbus Service Bulletin A300–53–
0218 as the appropriate source of
service information for accomplishing
certain actions. The procedures in
Revision 02 are essentially the same as
those in Revision 1, except that Revision
02 reduces the repetitive intervals for
the eddy current inspections of the
auxiliary power unit (APU) bleed-air
line, removes certain airplanes from the
inspection of the area between STGR 25
LH and RH, and removes certain
airplanes from the inspection of the area
between STGR 26 LH and RH.
Clarification of 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 comments
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 (at an average labor rate
of $65 per hour) for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Models
Action
Work hours 1
Parts 1
Cost per airplane 1
A300–600 series airplanes.
Modification ..........
Concurrent Actions 1.
Modification ..........
Concurrent Actions 1.
34 .........................
Between 590 and
660.
34 .........................
Between 590 and
660.
$1,200 ..................
Between $2,442
and $9,884.
$1,200 ..................
Between $2,442
and $9,884.
$3,410 ..................
Between $40,792
and $52,784.
$3,410 ..................
Between $40,792
and $52,784.
A310 series airplanes.
1 The
0
0
52
52
Fleet cost 1
$0.
$177,320.
Between $2,121,184 and
$2,744,768.
number of work hours and estimated costs for concurrent actions depend on airplane configuration.
Authority for This Rulemaking
rmajette on PROD1PC67 with RULES1
Number of
U.S.registered
airplanes
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.
VerDate Aug<31>2005
14:48 Oct 26, 2006
Jkt 211001
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
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
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
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Federal Register / Vol. 71, No. 208 / Friday, October 27, 2006 / Rules and Regulations
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.
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 adding the following new
airworthiness directive (AD):
I
2006–22–03 Airbus: Amendment 39–14800.
Docket No. FAA–2005–21343;
Directorate Identifier 2004–NM–117–AD.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Effective Date
(a) This AD becomes effective December 1,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300
B4–600, B4–600R, and F4–600R series
airplanes, and Model C4–605R Variant F
airplanes (collectively called A300–600
series airplanes); and Model A310 series
airplanes; certificated in any category; except
those modified in production by Airbus
Modification 6788.
Unsafe Condition
(d) This AD results from severe corrosion
found in the lower rim area of the aft
pressure bulkhead during routine
maintenance of an airplane. We are issuing
this AD to prevent corrosion on the inner rim
angle and cleat profile splice of the aft
pressure bulkhead, which could result in the
loss of airplane structural integrity.
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.
Service Bulletin References
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of the following service bulletins
listed in Table 1 of this AD, as applicable:
TABLE 1.—SERVICE BULLETIN REFERENCES
Models
Requirement
A300–600 series airplanes .............
A310 series airplanes .....................
Paragraph
Paragraph
Paragraph
Paragraph
rmajette on PROD1PC67 with RULES1
Modification To Improve Corrosion
Protection and Drainage
(g) Within 60 months after the effective
date of this AD, modify the aft pressure
bulkhead for improved corrosion protection
and drainage by doing all of the actions
specified in the Accomplishment
Instructions of the applicable service
bulletin. Where the service bulletin specifies
to use sealant PR–2752 (consumable material
list (CML) 09–035), sealant MC–650B (CML
09–056) may be used.
Concurrent Modification To Improve
Attachment Angles
(h) Before or concurrently with
accomplishing the modification required by
paragraph (g) of this AD, modify the aft
pressure bulkhead to improve the fatigue life
of the attachment angles at frame (FR) 80/82
by doing all of the actions specified in the
Accomplishment Instructions of the
applicable service bulletin. Where the service
bulletin specifies doing a visual inspection
around the entire circumference between
FR80/82 and the aft pressure bulkhead for
damaged filler, do a general visual
inspection.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
VerDate Aug<31>2005
14:48 Oct 26, 2006
Jkt 211001
(g)
(h)
(g)
(h)
of
of
of
of
this
this
this
this
AD
AD
AD
AD
Airbus service bulletin
...............
...............
...............
...............
A300–53–6017,
A300–53–6006,
A310–53–2036,
A310–53–2025,
Revision
Revision
Revision
Revision
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
Credit for Concurrent Actions
(i) For Model A310 series airplanes,
accomplishment of the actions specified in
paragraph A.2. of AD 88–06–03, amendment
39–5871 (53 FR 7730, March 10, 1988), is
considered acceptable for compliance with
the requirements of paragraph (h) of this AD.
Credit for Previous Service Bulletins
(j) Actions done before the effective date of
this AD in accordance with Airbus Service
Bulletin A310–53–2036, Revision 01, dated
October 9, 2003 (for Model A310 series
airplanes), are acceptable for compliance
with the requirements of paragraph (g) of this
AD.
(k) Actions done before the effective date
of this AD in accordance with Airbus Service
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
02, dated February 25, 2004.
3, dated March 24, 1989.
02, dated February 25, 2004.
06, dated August 3, 2006.
Bulletin A310–53–2025, Revision 5, dated
March 24, 1989 (for Model A310 series
airplanes), are acceptable for compliance
with the requirements of paragraph (h) of this
AD.
Alternative Methods of Compliance
(AMOCs)
(l)(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.
Related Information
(m) French airworthiness directive F–
2004–004, dated January 7, 2004, also
addresses the subject of this AD.
Material Incorporated by Reference
(n) You must use the applicable service
information identified in Table 2 of this AD
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
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Federal Register / Vol. 71, No. 208 / Friday, October 27, 2006 / Rules and Regulations
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE
Revision
level
Service bulletin
Airbus
Airbus
Airbus
Airbus
Service
Service
Service
Service
Bulletin,
Bulletin,
Bulletin,
Bulletin,
A300–53–6006
A300–53–6017
A310–53–2025
A310–53–2036
...............................................................................................................
...............................................................................................................
...............................................................................................................
...............................................................................................................
3
02
06
02
Date
March 24, 1989.
February 25, 2004.
August 3, 2006.
February 25, 2004.
Airbus Service Bulletin, A300–53–6006,
Revision 3, dated March 24, 1989, contains
the following effective pages:
Revision
level shown
on page
Page Nos.
1, 29, 47, 48 .....................................................................................................................................................
2–28, 30–46, 49–52 .........................................................................................................................................
The Director of the Federal Register
approved the incorporation by reference of
these documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. 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.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Airbus Model A300 and A310 airplanes
and A300–600 series airplanes. This AD
requires inspecting for discrepancies of
all electrical bundles located in the
leading and trailing edges of the wings,
and performing corrective actions if
necessary. This AD results from fuel
system reviews conducted by the
manufacturer. We are issuing this AD to
prevent an ignition source, which, in
combination with flammable fuel
vapors, could result in a fuel tank
explosion and consequent loss of the
airplane.
Issued in Renton, Washington, on October
11, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–17661 Filed 10–26–06; 8:45 am]
DATES:
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2006–25221; Directorate
Identifier 2006–NM–122–AD; Amendment
39–14804; AD 2006–22–07]
rmajette on PROD1PC67 with RULES1
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 and A310 Airplanes; and Airbus
Model A300 B4–600, B4–600R, and F4–
600R Series Airplanes, and Model C4–
605R Variant F Airplanes (Collectively
Called A300–600 Series Airplanes)
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
VerDate Aug<31>2005
14:48 Oct 26, 2006
Jkt 211001
This AD becomes effective
December 1, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 1, 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 Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
3
2
Date shown on page
March 24, 1989.
August 11, 1988.
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to all Airbus Model A300 and
A310 airplanes and A300–600 series
airplanes. That NPRM was published in
the Federal Register on June 30, 2006
(71 FR 37512). That NPRM proposed to
require inspecting for discrepancies of
all electrical bundles located in the
leading and trailing edges of the wings,
and performing corrective actions if
necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received.
Request To Change Incorporation of
Certain Information
The Modification and Replacement
Parts Association (MARPA) states that,
typically, airworthiness directives are
based on service information originating
with the type certificate holder or its
suppliers. MARPA adds that
manufacturer service documents are
privately authored instruments
generally having copyright protection
against duplication and distribution.
MARPA notes that when a service
document is incorporated by reference
into a public document, such as an
airworthiness directive, it loses its
private, protected status and becomes a
E:\FR\FM\27OCR1.SGM
27OCR1
]]>Agencies
[Federal Register Volume 71, Number 208 (Friday, October 27, 2006)]
[Rules and Regulations]
[Pages 62890-62895]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-17661]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21343; Directorate Identifier 2004-NM-117-AD;
Amendment 39-14800; AD 2006-22-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and
F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes
(Collectively Called A300-600 Series Airplanes); and Model A310 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
[[Page 62891]]
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus models, as specified above. This AD requires modifying
the aft pressure bulkhead for improved corrosion protection and
drainage, and related concurrent actions. This AD results from severe
corrosion found in the lower rim area of the aft pressure bulkhead
during routine maintenance of an airplane. We are issuing this AD to
prevent corrosion on the inner rim angle and cleat profile splice of
the aft pressure bulkhead, which could result in the loss of airplane
structural integrity.
DATES: This AD becomes effective December 1, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 1,
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 Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Airbus Model
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R
Variant F airplanes (collectively called A300-600 series airplanes);
and Model A310 series airplanes. That NPRM was published in the Federal
Register on June 3, 2005 (70 FR 32547). That NPRM proposed to require
modifying the aft pressure bulkhead for improved corrosion protection
and drainage, and related concurrent actions.
Actions Since NPRM Was Issued
Since we issued the NPRM, Airbus has released Service Bulletin
A310-53-2025, Revision 06, dated August 3, 2006. In the NPRM, we
referred to Airbus Service Bulletin A310-53-2025, Revision 5, dated
March 24, 1989, as the appropriate source of service information for
modifying the aft pressure bulkhead to improve the fatigue life of the
attachment angles at frame (FR)80/82 on Model A310 series airplanes.
The procedures in Revision 06 are essentially the same as those in
Revision 5. Therefore, we have revised Table 1 of this AD to refer to
Revision 06 as the appropriate source of service information for
accomplishing the modification on Model A310 series airplanes. We have
also added a new paragraph (k) to this AD, which gives credit for
actions accomplished before the effective date of this AD in accordance
with Revision 5.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Use Alternative Sealant
FedEx requests that we revise the NPRM to identify an alternative
to sealant PR-2752 (consumable material list (CML) 09-035), since it is
not available from any worldwide source. FedEx states that Airbus has
identified an alternative sealant for use on FedEx's airplanes.
However, that sealant has an 1,800-flight-cycle life limit, which
creates an undue burden on FedEx's operational planning of airplane
downtime and resources. FedEx also states that the FAA issued
alternative method of compliance (AMOC) letter ANM-116-04-175, dated
May 27, 2004, allowing use of that same alternative sealant, which
requires repetitively resealing the applicable areas within intervals
of 1,800 flight cycles. FedEx asserts that sealant PR-2752, due to its
brittleness and low elongation properties, tends to separate from the
structure, creating a moisture trap that leads to corrosion. FedEx
proposes substituting sealant PR-2752 with an epoxy adhesive like 3M
Scotch-Weld EC-2216 to maintain an adequate level of safety and meet
design parameters.
We partially agree. Since we issued the NPRM, Airbus has identified
another alternative to sealant PR-2752. Sealant MC-650B (CML 09-056),
from Chemetall, should be available in December of 2006. Airbus Service
Bulletin A310-53-2025, Revision 06, which we described previously,
already specifies using MC-650B. Although Airbus Service Bulletin A300-
53-6006, Revision 3, dated March 24, 1989, specifies using sealant PR-
2752, Airbus does not intend to revise this service bulletin because
all affected Model A300-600 series airplanes have been modified
already. Airbus has advised us that it does intend to revise Airbus
Service Bulletins A300-53-6017 and A310-53-2036, both Revision 02, both
dated February 25, 2004, to specify using sealant MC-650B. We have
revised paragraph (g) of this AD to allow use of sealant MC-650B as an
alternative to sealant PR-2752.
Request To Withdraw NPRM
FedEx requests that we withdraw the NPRM. As justification, FedEx
states that, due to the complex structural configuration of the aft
pressure bulkhead between FR80 and FR82 and the use of several
different compounds for modification of the drain hole, the referenced
service bulletins in the NPRM need to identify additional work
instructions and substitute materials. In addition, FedEx asserts that
removal of sealants, especially sealant PR-2752, could cause more
surface protection damage because of the complexity of the joint. FedEx
further requests that we coordinate with the Direction Generale de
l'Aviation Civile (DGAC), which is the airworthiness authority for
France, to ask Airbus to develop a better solution for the application
of corrosion-inhibiting compounds and sealants in the discrepant area.
We do not agree to withdraw the NPRM. As stated previously, Airbus
has either revised or intends to revise the referenced service
bulletins to identify an alternative sealant. Also, the revised service
bulletins use specific indicators and criteria to avoid removing the
sealant if it is not necessary. These changes should alleviate the
complexity of the service bulletins. We have not changed this AD in
this regard.
Request To Harmonize Various Service Bulletins and ADs
FedEx requests that we harmonize the modification and inspection
programs of several service bulletins and ADs that address corrosion in
the aft pressure bulkhead. For Model A300-600 series airplanes, FedEx
cites Airbus Service Bulletins A300-53-6006, Revision 3, dated March
24, 1989; A300-53-6017, Revision 02, dated February 25, 2004; and A300-
53-6136, dated October 27, 2004. For Model A310 series airplanes, FedEx
cites Airbus Service Bulletins
[[Page 62892]]
A310-53-2025, Revision 5, dated March 24, 1989; A310-53-2036, Revision
02, dated February 25, 2004; and A310-53-2114, dated October 27, 2004.
FedEx also cites AD 88-06-03, amendment 39-5871 (53 FR 7730, March 10,
1988), and AD 98-19-22, amendment 39-10763 (63 FR 49656, September 17,
1998).
We disagree and have not revised this AD in this regard. Although
the various service bulletins and ADs involve work in the area of the
aft pressure bulkhead, they address unsafe conditions related to either
corrosion or fatigue. Also, the affected airplanes in the various
service bulletins and ADs are different. This AD and AD 88-06-03 both
refer to Airbus Service Bulletin A310-53-2025 as the appropriate source
of service information for modifying the attachment of the rear
pressure bulkhead to FR80/82. This AD requires Revision 06 of that
service bulletin, while AD 88-06-03 requires the original issue, dated
April 21, 1986, or Revision 3, dated April 7, 1987. However, we
specified in the NPRM that paragraph (i) of this AD provides credit for
accomplishment of paragraph A.2. of AD 88-06-03. AD 88-06-03 also
refers to Airbus Service Bulletin A310-53-2024, Revision 1, dated June
20, 1986; or Revision 3, dated February 17, 1987; as appropriate
sources of service information for accomplishing repetitive inspections
of the rear pressure bulkhead for cracks. We issued AD 88-06-03 to
improve the fatigue life of the attachment angles at FR80/82 on certain
Model A310 series airplanes.
AD 98-19-22 refers to Airbus Service Bulletins A300-53-6066 and
A310-53-2092, both dated October 16, 1996; and Revision 01, both dated
March 11, 1998; as appropriate sources of service information for
accomplishing repetitive inspections to detect corrosion of the lower
rim area of the aft pressure bulkhead. After we issued AD 98-19-22,
severe corrosion was found on certain airplanes that were inspected
previously in accordance with that AD. Based on those findings, we
determined that the inspection methods in AD 98-19-22 were obsolete and
inadequate, and that a new inspection program was necessary.
Subsequently, we issued AD 2005-26-16, amendment 39-14437 (70 FR 77307,
December 30, 2005), to supersede AD 98-19-22. The inspections required
by AD 98-19-22, which refers to Airbus Service Bulletins A300-53-6066
and A310-53-2092, were not retained in AD 2005-26-16. AD 2005-26-16
instead refers to Airbus Service Bulletins A300-53-6136, Revision 01,
dated July 18, 2005; and A310-53-2114, Revision 01, dated September 1,
2005; as the appropriate sources of service information for
accomplishing the actions in that AD. Further, Airbus has informed us
that it issued Airbus Service Bulletins A300-53-6136 and A310-53-2114
to supersede Airbus Service Bulletins A300-53-6066 and A310-53-2092.
The table below provides an overview of the ADs we have issued.
----------------------------------------------------------------------------------------------------------------
Refers to airbus
AD-- service bulletin-- Requiring-- Addressing--
----------------------------------------------------------------------------------------------------------------
88-06-03........................... A310-53-2024, Repetitive Fatigue.
Revision 1 and inspections.
Revision 3.
A310-53-2025, Modification......... Fatigue.
original issue and
Revision 3.
98-19-22 (superseded by AD 2005-26- A300-53-6066, Repetitive Corrosion.
16). original issue and inspections.
Revision 01.
A310-53-2092, Repetitive Corrosion.
original issue and inspections.
Revision 01.
2005-26-16......................... A300-53-6136, Repetitive Corrosion.
Revision 01. inspections with
reduced intervals.
A310-53-2114, Repetitive Corrosion.
Revision 01. inspections with
reduced intervals.
This AD............................ A300-53-6017, Modification......... Corrosion.
Revision 02. Modification......... Corrosion.
A310-53-2036, Modification......... Fatigue.
Revision 02. Modification......... Fatigue.
A300-53-6006,
Revision 3.
A310-53-2025,
Revision 06.
----------------------------------------------------------------------------------------------------------------
Request for Credit for Airbus Service Bulletins A300-53-6066 and A310-
53-2092
FedEx requests that we give credit for accomplishment of Airbus
Service Bulletins A300-53-6066 and A310-53-2092. FedEx states that
these service bulletins are referenced in AD 98-19-22 and also involve
the lower rim area of the pressure bulkhead.
We disagree. As discussed previously, the repetitive inspections
specified in Airbus Service Bulletins A300-53-6066 and A310-53-2092 are
obsolete and inadequate for addressing corrosion at the lower rim area
of the rear pressure bulkhead. Further, the referenced service
bulletins in this AD are intended to not only improve the corrosion
protection at the lower rim area of the aft pressure bulkhead, but to
also improve the fatigue life of the attachment angles at FR80/82. We
have not changed this AD in this regard.
Request To Refer to Airbus Service Bulletins A300-53-6136 and A310-53-
2114
FedEx requests that we revise Table 1 of the NPRM to refer to
Airbus Service Bulletins A300-53-6136 and A310-53-2114, both dated
October 27, 2004, instead of Airbus Service Bulletins A300-53-6006,
Revision 3, dated March 24, 1989 (for Model A300-600 series airplanes);
and A310-53-2025, Revision 5, dated March 24, 1989 (for Model A310
series airplanes). (In the NPRM, we referred to Airbus Service
Bulletins A300-53-6006, Revision 3; and A310-53-2025, Revision 5; as
appropriate sources of service information for accomplishing certain
related concurrent actions.) As justification, FedEx states that Airbus
Service Bulletins A300-53-6136 and A310-53-2114 were issued to address
incomplete adhesion of sealant and damage caused to surface protection
during cleaning of the drain hole, or during accomplishment of Airbus
Service Bulletins A300-53-6006 and A310-53-2025. FedEx states that
Airbus Service Bulletins A300-53-6136 and A310-53-2114 also involve
inspections for corrosion in the lower rim angle area of the rear
pressure bulkhead. FedEx further requests that we coordinate with
Airbus and the DGAC to address the apparent discrepancy between Airbus
Service Bulletins A300-53-6136 and A300-53-6006 and between Airbus
Service Bulletins and A310-53-2025 and A310-53-2114.
We do not agree to refer to Airbus Service Bulletins A300-53-6136
and A310-53-2114 in this AD. As stated previously, AD 2005-26-16
mandates
[[Page 62893]]
accomplishment of Revision 01 of Airbus Service Bulletins A300-53-6136
and A310-53-2114, as applicable. Airbus has informed us that Airbus
Service Bulletins A300-53-6136 and A310-53-2114 were issued to address
corrosion prevention, while Airbus Service Bulletins A300-53-6006 and
A310-53-2025 were issued to address an unsafe condition caused by
fatigue. Airbus has also informed us that Airbus Service Bulletins
A300-53-6136 and A310-53-2114 mention accomplishment of 6767yttyyAirbus
Service Bulletins A300-53-6006 and A310-53-2025 only as possible
sources for corrosion if surface protection is damaged. Airbus states
that the service bulletins must be accomplished independently of each
other. Therefore, we have not changed this AD in this regard.
Request for Credit for Airbus Service Bulletin A300-53-0218
The Air Transport Association (ATA), on behalf of its member ASTAR
Air Cargo (ASTAR), questions the basis of the NPRM since Airbus has
issued Service Bulletin A300-53-0218, Revision 02, dated May 10, 2005.
ASTAR states that it has accomplished Revision 02 of the service
bulletin and intends to use it to show compliance with the proposed
requirements of the NPRM. We infer that ASTAR would like us to revise
this AD to allow Airbus Service Bulletin A300-53-0218, Revision 02, as
an acceptable method of compliance.
We do not agree that Revision 02 of Airbus Service Bulletin A300-
53-0218 is acceptable for complying with the requirements of this AD.
For Model A300-600 series airplanes, this AD requires accomplishment of
Airbus Service Bulletins A300-53-6017, Revision 02; and A300-53-6006,
Revision 3. Airbus Service Bulletin A300-53-6017 describes procedures
for improving the corrosion protection at the aft pressure bulkhead and
enlarging the drainholes for improved drainage. Airbus Service Bulletin
A300-53-6006 describes procedures for modifying the aft pressure
bulkhead to improve the fatigue life of the attachment angles at FR80/
82. Airbus Service Bulletin A300-53-0218 describes procedures for
inspecting for corrosion and cracks in the upper rim area of the rear
pressure bulkhead aft face, between stringer (STGR) 26 left-hand (LH)
and right-hand (RH) and all service apertures, and removing corrosion
and repairing as necessary. The service bulletins address different
issues; therefore, we have not changed this AD in this regard.
We point out that Airbus Service Bulletin A300-53-218, Revision 1,
July 28, 1989, is mandated by AD 90-03-08, amendment 39-6481 (55 FR
1799, January 19, 1990). That AD applies to all Model A300 airplanes.
That AD requires repetitive inspections for cracking and corrosion in
the lower rim area of the rear pressure bulkhead and adjacent areas,
repetitive inspections for cracking or corrosion in the service
apertures and the upper rim area of the rear pressure bulkhead, and
corrective actions if necessary. We issued AD 90-03-08 to prevent
reduced structural capability of the fuselage and subsequent
decompression of the airplane. Since we issued AD 90-03-08, we have
issued an NPRM to supersede that AD. That NPRM was published in the
Federal Register on August 1, 2006 (71 FR 43386). That NPRM refers to
Revision 02 of Airbus Service Bulletin A300-53-0218 as the appropriate
source of service information for accomplishing certain actions. The
procedures in Revision 02 are essentially the same as those in Revision
1, except that Revision 02 reduces the repetitive intervals for the
eddy current inspections of the auxiliary power unit (APU) bleed-air
line, removes certain airplanes from the inspection of the area between
STGR 25 LH and RH, and removes certain airplanes from the inspection of
the area between STGR 26 LH and RH.
Clarification of 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
comments 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 (at an average
labor rate of $65 per hour) for U.S. operators to comply with this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Cost per airplane U.S.-
Models Action Work hours \1\ Parts \1\ \1\ registered Fleet cost \1\
airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
A300-600 series airplanes........ Modification........ 34................. $1,200............. $3,410............. 0 $0.
Concurrent Actions Between 590 and 660 Between $2,442 and Between $40,792 and 0 ...................
\1\. $9,884. $52,784.
A310 series airplanes............ Modification........ 34................. $1,200............. $3,410............. 52 $177,320.
Concurrent Actions Between 590 and 660 Between $2,442 and Between $40,792 and 52 Between $2,121,184
\1\. $9,884. $52,784. and $2,744,768.
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ The number of work hours and estimated costs for concurrent actions depend on airplane configuration.
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
[[Page 62894]]
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
adding the following new airworthiness directive (AD):
2006-22-03 Airbus: Amendment 39-14800. Docket No. FAA-2005-21343;
Directorate Identifier 2004-NM-117-AD.
Effective Date
(a) This AD becomes effective December 1, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 B4-600, B4-600R, and
F4-600R series airplanes, and Model C4-605R Variant F airplanes
(collectively called A300-600 series airplanes); and Model A310
series airplanes; certificated in any category; except those
modified in production by Airbus Modification 6788.
Unsafe Condition
(d) This AD results from severe corrosion found in the lower rim
area of the aft pressure bulkhead during routine maintenance of an
airplane. We are issuing this AD to prevent corrosion on the inner
rim angle and cleat profile splice of the aft pressure bulkhead,
which could result in the loss of airplane structural integrity.
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.
Service Bulletin References
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the following service bulletins
listed in Table 1 of this AD, as applicable:
Table 1.--Service Bulletin References
------------------------------------------------------------------------
Airbus service
Models Requirement bulletin
------------------------------------------------------------------------
A300-600 series airplanes..... Paragraph (g) of A300-53-6017,
this AD. Revision 02, dated
Paragraph (h) of February 25, 2004.
this AD. A300-53-6006,
Revision 3, dated
March 24, 1989.
A310 series airplanes......... Paragraph (g) of A310-53-2036,
this AD. Revision 02, dated
Paragraph (h) of February 25, 2004.
this AD. A310-53-2025,
Revision 06, dated
August 3, 2006.
------------------------------------------------------------------------
Modification To Improve Corrosion Protection and Drainage
(g) Within 60 months after the effective date of this AD, modify
the aft pressure bulkhead for improved corrosion protection and
drainage by doing all of the actions specified in the Accomplishment
Instructions of the applicable service bulletin. Where the service
bulletin specifies to use sealant PR-2752 (consumable material list
(CML) 09-035), sealant MC-650B (CML 09-056) may be used.
Concurrent Modification To Improve Attachment Angles
(h) Before or concurrently with accomplishing the modification
required by paragraph (g) of this AD, modify the aft pressure
bulkhead to improve the fatigue life of the attachment angles at
frame (FR) 80/82 by doing all of the actions specified in the
Accomplishment Instructions of the applicable service bulletin.
Where the service bulletin specifies doing a visual inspection
around the entire circumference between FR80/82 and the aft pressure
bulkhead for damaged filler, do a general visual inspection.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
Credit for Concurrent Actions
(i) For Model A310 series airplanes, accomplishment of the
actions specified in paragraph A.2. of AD 88-06-03, amendment 39-
5871 (53 FR 7730, March 10, 1988), is considered acceptable for
compliance with the requirements of paragraph (h) of this AD.
Credit for Previous Service Bulletins
(j) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletin A310-53-2036, Revision 01,
dated October 9, 2003 (for Model A310 series airplanes), are
acceptable for compliance with the requirements of paragraph (g) of
this AD.
(k) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletin A310-53-2025, Revision 5,
dated March 24, 1989 (for Model A310 series airplanes), are
acceptable for compliance with the requirements of paragraph (h) of
this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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.
Related Information
(m) French airworthiness directive F-2004-004, dated January 7,
2004, also addresses the subject of this AD.
Material Incorporated by Reference
(n) You must use the applicable service information identified
in Table 2 of this AD to perform the actions that are required by
this AD, unless the AD specifies otherwise.
[[Page 62895]]
Table 2.--Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Service bulletin level Date
------------------------------------------------------------------------
Airbus Service Bulletin, A300- 3 March 24, 1989.
53-6006.
Airbus Service Bulletin, A300- 02 February 25, 2004.
53-6017.
Airbus Service Bulletin, A310- 06 August 3, 2006.
53-2025.
Airbus Service Bulletin, A310- 02 February 25, 2004.
53-2036.
------------------------------------------------------------------------
Airbus Service Bulletin, A300-53-6006, Revision 3, dated March
24, 1989, contains the following effective pages:
------------------------------------------------------------------------
Revision
Page Nos. level shown Date shown on page
on page
------------------------------------------------------------------------
1, 29, 47, 48................. 3 March 24, 1989.
2-28, 30-46, 49-52............ 2 August 11, 1988.
------------------------------------------------------------------------
The Director of the Federal Register approved the incorporation
by reference of these documents in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. 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 October 11, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-17661 Filed 10-26-06; 8:45 am]
BILLING CODE 4910-13-P
