Airworthiness Directives; Airbus Model A300 Airplanes, 43386-43390 [E6-12301]
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43386
Federal Register / Vol. 71, No. 147 / Tuesday, August 1, 2006 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25423; Directorate
Identifier 2006–NM–029–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
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AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Airbus
Model A300 airplanes. The existing AD
currently 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. This
proposed AD would remove certain
repetitive inspections and reduce the
repetitive interval of one inspection.
This proposed AD would also require an
inspection for missing or damaged
sealant of the area between the outer
attachment angle and circumferential
joint doubler, and corrective action if
necessary. This proposed AD would
also require additional inspections for
corrosion of certain areas and repetitive
inspections for airplanes on which
repairs have been done. This proposed
AD results from reports of corrosion and
cracking in the various components
associated with the rear pressure
bulkhead. We are proposing this AD to
prevent reduced structural capability of
the fuselage and consequent
decompression of the airplane.
DATES: We must receive comments on
this proposed AD by August 31, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
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• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France
for service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT:
Thomas Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘Docket No. FAA–2006–25423;
Directorate Identifier 2006–NM–029–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
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Discussion
On January 8, 1990, we issued AD 90–
03–08, amendment 39–6481 (55 FR
1799, January 19, 1990), for all Airbus
Model A300 series 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. That AD resulted
from reports of corrosion and cracking
in the various components associated
with the rear pressure bulkhead. We
issued that AD to prevent reduced
structural capability of the fuselage and
subsequent decompression of the
airplane.
Actions Since Existing AD Was Issued
Since we issued AD 90–03–08, we
have issued AD 2005–26–16,
amendment 39–14437 (70 FR 77307,
December 30, 2005), for certain Airbus
Model A300 B2 and A300 B4 series
airplanes; A300 B4–600, B4–600R, and
F4–600R series airplanes, and C4–605R
Variant F airplanes (collectively called
A300–600 series airplanes); and Airbus
Model A310–200 and A310–300 series
airplanes. That AD requires repetitive
inspections for corrosion on the rear
pressure bulkhead between stringer
(STGR) 27 right hand (RH) and STGR 27
left hand (LH), and related investigative
and corrective actions if necessary. The
inspections for the Model A300 B2 and
A300 B4 series airplanes are done in
accordance with Airbus Service Bulletin
A300–53–0363, Revision 01, dated June
10, 2005. Service bulletin A300–53–
0363 supersedes Airbus Service Bulletin
A300–53–0217, which is cited as an
appropriate source of service
information for doing the actions
required by paragraphs A., B., and C. of
AD 90–03–08. Therefore, we have not
included the requirements of paragraphs
A., B., and C. of AD 90–03–08 in this
proposed AD.
Relevant Service Information
Airbus has issued service bulletin
A300–53–0218, Revision 02, dated May
10, 2005. Airbus Service Bulletin A300–
53–218, Revision 1, dated July 28, 1989,
is cited as an appropriate source of
service information for doing certain
inspections required by AD 90–03–08.
Revision 2 of the service bulletin
describes the following procedures:
• Repetitive inspections for corrosion
and cracking of the upper rim area of
the rear pressure bulkhead from the aft
face.
• Repetitive eddy current inspections
for cracks and corrosion from the
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outboard side in certain areas, as
applicable.
• Repetitive inspections for cracks
and corrosion of the service apertures in
the rear pressure bulkhead.
• Repetitive eddy current inspections
for cracks and corrosion of the apertures
for the auxiliary power unit (APU)
bleed-air and fuel.
• Repetitive inspections of the area
between the outer attachment angle and
circumferential joint doubler to
determine if sealant is missing or
damaged.
• If any cracking or corrosion is found
during an inspection, the service
bulletin specifies doing a repair or
contacting the manufacturer.
Revision 02 of the service bulletin
provides basically the same procedures
as Revision 1 for the inspections for
corrosion and cracking in the area of the
rear pressure bulkhead, and repair if
necessary. However, Revision 02 of the
service bulletin specifies reduced
repetitive intervals for the eddy current
inspections of the APU bleed-air line.
Revision 02 also removes certain
airplanes from the inspection of the area
between STGR 25 LH and RH and
certain other airplanes from the
inspection of the area between STGR 26
LH and RH.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
´ ´
condition. The Direction Generale de
l’Aviation Civile (DGAC), which is the
airworthiness authority for France,
mandated the service information and
issued French airworthiness directive
F–2005–093 R1, dated August 3, 2005,
to ensure the continued airworthiness of
these airplanes in France.
FAA’s Determination and Requirements
of the Proposed AD
This airplane model is manufactured
in France and is type certificated for
operation in the United States under the
provisions of § 21.29 of the Federal
Aviation Regulations (14 CFR 21.29)
and the applicable bilateral
airworthiness agreement. Pursuant to
this bilateral airworthiness agreement,
the DGAC has kept the FAA informed
of the situation described above. We
have examined the DGAC’s findings,
evaluated all pertinent information, and
determined that AD action is necessary
for airplanes of this type design that are
certificated for operation in the United
States.
This proposed AD would supersede
AD 90–03–08 and would remove certain
requirements of the existing AD. This
proposed AD would also reduce the
repetitive interval of the eddy current
inspections of the APU bleed-air line.
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This proposed AD would also require an
inspection for missing or damaged
sealant of the area between the outer
attachment angle and circumferential
joint doubler, and corrective action if
necessary. This proposed AD would
also require additional inspections for
corrosion of certain areas and repetitive
inspections for airplanes on which
repairs have been done.
Differences Between the Proposed AD
and the Service Bulletin
Unlike the procedures described in
the service bulletin, this proposed AD
would not permit further flight if cracks
or corrosion are detected within limits
specified in the service bulletin. We
have determined that, because of the
safety implications and consequences
associated with that cracking or
corrosion, repairs must be done before
further flight.
The service bulletin specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions using
a method that we or the European
Aviation Safety Agency (EASA) (or its
delegated agent) approve. In light of the
type of repair that would be required to
address the unsafe condition, and
consistent with existing bilateral
airworthiness agreements, we have
determined that, for this proposed AD,
a repair we or the EASA approve would
be acceptable for compliance with this
proposed AD.
The service bulletin specifies to
‘‘visually inspect’’ for missing or
damaged sealant. We have determined
that this inspection should be described
as a ‘‘general visual inspection.’’ Note 2
has been included in this proposed AD
to define this type of inspection.
Clarification of Requirement of Certain
Inspections
Airbus Service Bulletin A300–53–218,
Revision 1, describes repetitive
inspections of the area between the
outer attachment angle and
circumferential joint doubler to
determine if sealant is missing or
damaged and corrective action if
necessary. The corrective action
includes removing damaged sealant and
applying new sealant to areas where
sealant is missing or removed. AD 90–
03–08 did not specifically require that
inspection. Revision 02 of Airbus
Service Bulletin A300–53–0218 also
includes the inspection for missing or
damaged sealant. To ensure that the
inspection is being done we have added
paragraphs (i) and (j) to this proposed
AD. Doing this inspection and
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corrective action addresses the
identified unsafe condition.
Airbus Service Bulletin A300–53–218,
Revision 1, describes procedures for
doing initial and repetitive nondestructive test (NDT) inspections for
corrosion and cracks of the outboard
sides of certain stringers and of the
apertures for the APU bleed-air and fuel.
AD 90–03–08 did not require an
inspection for corrosion of those areas
(AD 90–03–08 requires NDT inspections
of those areas for cracking only; certain
NDT inspections cannot detect
corrosion). Revision 02 of Airbus
Service Bulletin A300–53–0218 also
specifies procedures to do NDT
inspections of those areas for cracking
and corrosion. To inspect those areas for
corrosion, detailed visual inspections
must be done. Therefore, paragraph (l)
has been included in this proposed AD
to clarify that, for eddy current (NDT)
inspections performed after the effective
date of this AD, accomplishment of a
detailed inspection for corrosion must
be done at the same time as the eddy
current inspection.
Clarification of Actions in AD 90–03–08
In paragraphs D.1.a. and E.1. of AD
90–03–08 we specify doing initial and
repetitive X-ray inspections for cracking
of the rim area of the rear pressure
bulkhead as a separate action. Upon
further review of Airbus Service
Bulletin A300–53–218, Revision 1, we
have determined that these inspections
are related investigative actions to the
eddy current inspections specified in
paragraphs D.1.c. and E.3 of AD 90–03–
08. Paragraph 3.B. (4) of Revision 02 of
Airbus Service Bulletin A300–53–0218
describes these inspections in the same
manner. Therefore, we have removed
the X-ray inspection specified in the
existing AD and added paragraph (l) to
this proposed AD to ensure that this
inspection is done, if necessary,
depending on the results of the
inspections specified in paragraphs
(f)(2) and (h)(2) of this AD (specified as
paragraphs D.1c. and E.3 of AD 90–03–
08).
Revision 02 of Airbus Service Bulletin
A300–53–0218 removes MSN 002 from
the inspection of the area between STGR
25 LH and RH and removes MSNs 009
through 018 from the inspection of the
area between STGR 26 LH and RH. We
have revised paragraphs (f)(2)(i) and
(f)(2)(ii) accordingly.
Changes to Existing AD
This proposed AD would retain
certain requirements of AD 90–03–08.
Since AD 90–03–08 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
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result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
90–03–08
Paragraph D ..............
Paragraph E ..............
Paragraph F ..............
Corresponding requirement in this proposed AD
Paragraphs (f) and
(g).
Paragraph (h).
Paragraph (n).
Explanation of Change to Applicability
We have changed the airplane model
designations in the applicability of this
proposed AD to be consistent with the
parallel French airworthiness directive.
Explanation of Change Made to Existing
Requirements
this proposed AD. We have included the
definition for a detailed inspection in
Note 1 of this proposed AD.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
Where the service bulletin specifies to
‘‘visually inspect,’’ except for the
inspection for missing or damaged
sealant, and where AD 90–03–08
specifies to do a ‘‘visual inspection,’’ we
specify to do a ‘‘detailed inspection’’ in
ESTIMATED COSTS
Action
Work hours
Inspections (required by AD
90–03–08).
New Inspections (required by
this AD).
Fleet cost
$800, per inspection cycle .....
51
$40,800, per inspection cycle.
10
80
800, per inspection cycle .......
51
$40,800, per inspection cycle.
Regulatory Findings
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Number of
U.S.-registered
airplanes
$80
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.
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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Cost per airplane
10
Authority for This Rulemaking
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2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
Comments Due Date
(a) The FAA must receive comments on
this AD action by August 31, 2006.
Affected ADs
(b) This AD supersedes AD 90–03–08.
Applicability
Air transportation, Aircraft, Aviation
safety, Safety.
(c) This AD applies to all Airbus Model
A300 airplanes, certificated in any category;
except the following airplanes:
(1) Model A300 B4–601, B4–603, B4–620,
and B4–622 airplanes;
(2) Model A300 B4–605R and B4–622R
airplanes;
(3) Model A300 F4–605R and F4–622R
airplanes; and
(4) Airbus Model A300 C4–605R Variant F
airplanes.
The Proposed Amendment
Unsafe Condition
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
(d) This AD results from reports of
corrosion and cracking in the various
components associated with the rear pressure
bulkhead. We are issuing this AD to prevent
reduced structural capability of the fuselage
and consequent decompression of the
airplane.
List of Subjects in 14 CFR Part 39
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–6481 (55
FR 1799, January 19, 1990) and adding
the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2006–25423;
Directorate Identifier 2006–NM–029–AD.
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Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD
90–03–08 With New Repetitive Intervals
Initial Inspections
(f) Within the time limits specified in
paragraph (g) of this AD, conduct the
inspections specified in paragraphs (f)(1)
through (f)(4) of this AD in accordance with
Airbus Service Bulletin
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A300–53–218, Revision 1, dated July 28,
1989; or Airbus Service Bulletin A300–53–
0218, Revision 02, dated May 10, 2005. After
the effective date of this AD, Airbus Service
Bulletin A300–53–0218, Revision 02, dated
May 10, 2005, must be used.
(1) Perform a detailed inspection for
corrosion and cracking of the upper rim area
of the rear pressure bulkhead from the aft
face.
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.’’
(2) Perform an eddy current inspection for
cracks from the outboard side in the
applicable areas specified in paragraph
(f)(2)(i) or (f)(2)(ii) of this AD.
(i) For airplanes, manufacturer’s serial
number (MSN) 003 through 008: Between
Stringer (STGR) 25 left hand (LH) and right
hand (RH).
(ii) For airplanes, MSN 019 through 305:
Between STGR 26 LH and RH.
(3) Perform a detailed inspection for cracks
and corrosion of the service apertures in the
rear pressure bulkhead.
(4) Perform an eddy current inspection for
cracks of the apertures for the auxiliary
power unit (APU) bleed-air and fuel.
(g) At the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD, do the
inspections required by paragraph (f) of this
AD.
(1) For airplanes having accumulated
26,000 landings or fewer as of February 23,
1990 (the effective date of AD 90–03–08):
Perform the initial inspections required by
paragraph (f) of this AD, prior to the
accumulation of 24,000 landings or within
2,000 landings after February 23, 1990,
whichever occurs later.
(2) For airplanes having accumulated more
than 26,000 landings as of February 23, 1990:
Perform the initial inspections required by
paragraph (f) of this AD, within 1,000
landings after February 23, 1990.
Repetitive Inspections
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(h) If no cracking or corrosion is found
during the inspections required by paragraph
(f) of this AD, repeat the inspections
specified in paragraphs (h)(1), (h)(2), (h)(3),
(h)(4), and (h)(5) of this AD thereafter at the
times specified in the paragraphs.
(1) Repeat the detailed inspections of the
upper rim area specified in paragraph (f)(1)
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of this AD thereafter at intervals not to
exceed 8,000 landings.
(2) Repeat the eddy current inspection
from the outboard side between STGR 25 LH
and RH, or STGR 26 LH and RH, as
applicable, specified in paragraph (f)(2) of
this AD thereafter at intervals not to exceed
8,000 landings.
(3) Repeat the detailed inspection of the
service apertures specified in paragraph (f)(3)
of this AD thereafter at intervals not to
exceed 6,000 landings.
(4) Repeat eddy current inspections of APU
fuel apertures specified in paragraph (f)(4) of
this AD thereafter at intervals not to exceed
6,000 landings.
(5) At the earlier of the times specified in
paragraph (g)(5)(i) and (g)(5)(ii) of this AD, do
the eddy current inspection of the APU
bleed-air line service aperture specified in
paragraph (f)(4) of this AD. Repeat the
inspection thereafter at intervals not to
exceed 6,000 landing.
(i) Within 12,000 landings since the last
inspection of the APU bleed-air line service
aperture specified in paragraph (f)(4) of this
AD.
(ii) Within 6,000 landings since the last
inspection of the APU bleed-air line service
aperture specified in paragraph (f)(4) of this
AD or within 2,000 landings after the
effective date of this AD, whichever occurs
later.
New Requirements of This AD
Inspection for Sealant and Corrective Action
(i) Within the time limits specified in
paragraph (j) of this AD: Do a general visual
inspection of the area between the outer
attachment angle and circumferential joint
doubler to determine if sealant is missing or
damaged and do all applicable corrective
actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–0218, Revision 02,
dated May 10, 2005. Do all applicable
corrective actions before further flight.
Repeat the inspection thereafter at intervals
not to exceed 6,000 landings.
Note 2: 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,
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ladders, or platforms may be required to gain
proximity to the area being checked.’’
(j) At the applicable time specified in
paragraph (j)(1) or (j)(2) of this AD, do the
inspections required by paragraph (i) of this
AD.
(1) For airplanes having accumulated
26,000 landings or fewer as of the effective
date of this AD): Perform the initial
inspection required by paragraph (i) of this
AD, prior to the accumulation of 24,000
landings or within 2,000 landings after the
effective date of this AD, whichever occurs
later.
(2) For airplanes having accumulated more
than 26,000 landings as of the effective date
of this AD: Perform the initial inspection
required by paragraph (i) of this AD, within
1,000 landings after the effective date of this
AD.
Additional Inspections
(k) For airplanes on which the inspections
specified in paragraphs (f)(2), (f)(4), (h)(2),
and (h)(4) of this AD are accomplished after
the effective date of this AD: Where this AD
requires an eddy current inspection for
cracks, do a detailed inspection for corrosion
at the same time as the eddy current
inspection for cracks in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–0218, Revision 02,
dated May 10, 2005.
(l) For airplanes on which the inspections
specified in paragraphs (f)(2) and (h)(2) of
this AD are accomplished after the effective
date of this AD: If any crack is found during
any inspection required by paragraph (f)(2) or
(h)(2), before further flight, do an X-ray
inspection for cracking of the rim area of the
rear pressure bulkhead in the area of STGR
21 LH and RH in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–0218, Revision 02,
dated May 10, 2005.
New Repetitive Inspections
(m) For airplanes on which a repair has
been done in accordance with Airbus Service
Bulletin A300–53–218, Revision 1, dated July
28, 1989; or Airbus Service Bulletin A300–
53–0218, Revision 02, dated May 10, 2005;
before the effective date of this AD: At the
later of the times specified in paragraphs
(m)(1) and (m)(2) of this AD, do the
inspections specified in paragraphs (h), (k),
and (l) of this AD. Repeat the inspections
specified in paragraphs (h), (k), and (l) of this
AD thereafter at the applicable times
specified in paragraph (h).
(1) Within the times specified in paragraph
(h) of this AD.
(2) Within 2,000 landings after the effective
date of this AD.
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Corrective Actions for Cracking and
Corrosion and Repetitive Inspections
(n) If cracking or corrosion is found during
any inspection required by paragraph (f), (h),
(k), (l) or (m) of this AD, repair prior to
further flight, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–218, Revision 1,
dated July 28, 1989; or Airbus Service
Bulletin A300–53–0218, Revision 02, dated
May 10, 2005. As of the effective date of this
AD, do the repair in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–0218, Revision 02,
dated May 10, 2005; except where the service
bulletin specifies to contact the manufacturer
to repair certain conditions, this AD requires
repairing those conditions using a method
approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent). As of the effective date of
this AD, repeat the inspections specified in
paragraphs (h), (k), and (l) of this AD
thereafter at the applicable times specified in
paragraph (h).
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) AMOCs approved previously in
accordance with AD 90–03–08 are not
approved as AMOCs with this AD.
Related Information
French airworthiness directive F–2005–093
R1, dated August 3, 2005, also addresses the
subject of this AD.
Issued in Renton, Washington, on July 21,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–12301 Filed 7–31–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25470; Directorate
Identifier 2006–NM–090–AD]
hsrobinson on PROD1PC70 with PROPOSALS
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Aug<31>2005
15:05 Jul 31, 2006
Jkt 208001
Notice of proposed rulemaking
(NPRM).
ACTION:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Boeing Model 747–400 series airplanes.
The existing AD currently requires
replacement of the decompression
panels that are located in the smoke
barrier between the passenger and main
deck cargo compartment with new
panels of an improved design. This
proposed AD would require
modification of the decompression
panels on the smoke barrier in the main
deck cargo compartment or replacement
of the smoke barrier with an improved
smoke barrier, as applicable. This
proposed AD would also require
repetitive inspections of the
decompression (vent) panels on the
smoke barrier and corrective actions if
necessary. This proposed AD also adds
airplanes to the applicability. This
proposed AD results from reports of
decompression panels on the smoke
barrier opening in flight and on the
ground without a decompression event.
We are proposing this AD to prevent
inadvertent opening or tearing of
decompression panels, which could
result in degraded cargo fire detection
and suppression capability, smoke
penetration into an occupied
compartment, and an uncontrolled
cargo fire, if a fire occurs in the main
deck cargo compartment.
DATES: We must receive comments on
this proposed AD by September 15,
2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this proposed
AD.
PO 00000
Frm 00020
Fmt 4702
Sfmt 4702
FOR FURTHER INFORMATION CONTACT:
Susan Letcher, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6474; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘Docket No. FAA–2006–25470;
Directorate Identifier 2006–NM–090–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or visit https://dms.dot.gov.
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
E:\FR\FM\01AUP1.SGM
01AUP1
]]>Agencies
[Federal Register Volume 71, Number 147 (Tuesday, August 1, 2006)]
[Proposed Rules]
[Pages 43386-43390]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-12301]
[[Page 43386]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25423; Directorate Identifier 2006-NM-029-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Airbus Model A300 airplanes. The
existing AD currently 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. This proposed AD would remove
certain repetitive inspections and reduce the repetitive interval of
one inspection. This proposed AD would also require an inspection for
missing or damaged sealant of the area between the outer attachment
angle and circumferential joint doubler, and corrective action if
necessary. This proposed AD would also require additional inspections
for corrosion of certain areas and repetitive inspections for airplanes
on which repairs have been done. This proposed AD results from reports
of corrosion and cracking in the various components associated with the
rear pressure bulkhead. We are proposing this AD to prevent reduced
structural capability of the fuselage and consequent decompression of
the airplane.
DATES: We must receive comments on this proposed AD by August 31, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France for service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2006-25423; Directorate Identifier 2006-NM-029-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
On January 8, 1990, we issued AD 90-03-08, amendment 39-6481 (55 FR
1799, January 19, 1990), for all Airbus Model A300 series 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. That AD resulted from reports of
corrosion and cracking in the various components associated with the
rear pressure bulkhead. We issued that AD to prevent reduced structural
capability of the fuselage and subsequent decompression of the
airplane.
Actions Since Existing AD Was Issued
Since we issued AD 90-03-08, we have issued AD 2005-26-16,
amendment 39-14437 (70 FR 77307, December 30, 2005), for certain Airbus
Model A300 B2 and A300 B4 series airplanes; A300 B4-600, B4-600R, and
F4-600R series airplanes, and C4-605R Variant F airplanes (collectively
called A300-600 series airplanes); and Airbus Model A310-200 and A310-
300 series airplanes. That AD requires repetitive inspections for
corrosion on the rear pressure bulkhead between stringer (STGR) 27
right hand (RH) and STGR 27 left hand (LH), and related investigative
and corrective actions if necessary. The inspections for the Model A300
B2 and A300 B4 series airplanes are done in accordance with Airbus
Service Bulletin A300-53-0363, Revision 01, dated June 10, 2005.
Service bulletin A300-53-0363 supersedes Airbus Service Bulletin A300-
53-0217, which is cited as an appropriate source of service information
for doing the actions required by paragraphs A., B., and C. of AD 90-
03-08. Therefore, we have not included the requirements of paragraphs
A., B., and C. of AD 90-03-08 in this proposed AD.
Relevant Service Information
Airbus has issued service bulletin A300-53-0218, Revision 02, dated
May 10, 2005. Airbus Service Bulletin A300-53-218, Revision 1, dated
July 28, 1989, is cited as an appropriate source of service information
for doing certain inspections required by AD 90-03-08. Revision 2 of
the service bulletin describes the following procedures:
Repetitive inspections for corrosion and cracking of the
upper rim area of the rear pressure bulkhead from the aft face.
Repetitive eddy current inspections for cracks and
corrosion from the
[[Page 43387]]
outboard side in certain areas, as applicable.
Repetitive inspections for cracks and corrosion of the
service apertures in the rear pressure bulkhead.
Repetitive eddy current inspections for cracks and
corrosion of the apertures for the auxiliary power unit (APU) bleed-air
and fuel.
Repetitive inspections of the area between the outer
attachment angle and circumferential joint doubler to determine if
sealant is missing or damaged.
If any cracking or corrosion is found during an
inspection, the service bulletin specifies doing a repair or contacting
the manufacturer.
Revision 02 of the service bulletin provides basically the same
procedures as Revision 1 for the inspections for corrosion and cracking
in the area of the rear pressure bulkhead, and repair if necessary.
However, Revision 02 of the service bulletin specifies reduced
repetitive intervals for the eddy current inspections of the APU bleed-
air line. Revision 02 also removes certain airplanes from the
inspection of the area between STGR 25 LH and RH and certain other
airplanes from the inspection of the area between STGR 26 LH and RH.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, mandated the service information
and issued French airworthiness directive F-2005-093 R1, dated August
3, 2005, to ensure the continued airworthiness of these airplanes in
France.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 90-03-08 and would remove
certain requirements of the existing AD. This proposed AD would also
reduce the repetitive interval of the eddy current inspections of the
APU bleed-air line. This proposed AD would also require an inspection
for missing or damaged sealant of the area between the outer attachment
angle and circumferential joint doubler, and corrective action if
necessary. This proposed AD would also require additional inspections
for corrosion of certain areas and repetitive inspections for airplanes
on which repairs have been done.
Differences Between the Proposed AD and the Service Bulletin
Unlike the procedures described in the service bulletin, this
proposed AD would not permit further flight if cracks or corrosion are
detected within limits specified in the service bulletin. We have
determined that, because of the safety implications and consequences
associated with that cracking or corrosion, repairs must be done before
further flight.
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions using a method that we or the
European Aviation Safety Agency (EASA) (or its delegated agent)
approve. In light of the type of repair that would be required to
address the unsafe condition, and consistent with existing bilateral
airworthiness agreements, we have determined that, for this proposed
AD, a repair we or the EASA approve would be acceptable for compliance
with this proposed AD.
The service bulletin specifies to ``visually inspect'' for missing
or damaged sealant. We have determined that this inspection should be
described as a ``general visual inspection.'' Note 2 has been included
in this proposed AD to define this type of inspection.
Clarification of Requirement of Certain Inspections
Airbus Service Bulletin A300-53-218, Revision 1, describes
repetitive inspections of the area between the outer attachment angle
and circumferential joint doubler to determine if sealant is missing or
damaged and corrective action if necessary. The corrective action
includes removing damaged sealant and applying new sealant to areas
where sealant is missing or removed. AD 90-03-08 did not specifically
require that inspection. Revision 02 of Airbus Service Bulletin A300-
53-0218 also includes the inspection for missing or damaged sealant. To
ensure that the inspection is being done we have added paragraphs (i)
and (j) to this proposed AD. Doing this inspection and corrective
action addresses the identified unsafe condition.
Airbus Service Bulletin A300-53-218, Revision 1, describes
procedures for doing initial and repetitive non-destructive test (NDT)
inspections for corrosion and cracks of the outboard sides of certain
stringers and of the apertures for the APU bleed-air and fuel. AD 90-
03-08 did not require an inspection for corrosion of those areas (AD
90-03-08 requires NDT inspections of those areas for cracking only;
certain NDT inspections cannot detect corrosion). Revision 02 of Airbus
Service Bulletin A300-53-0218 also specifies procedures to do NDT
inspections of those areas for cracking and corrosion. To inspect those
areas for corrosion, detailed visual inspections must be done.
Therefore, paragraph (l) has been included in this proposed AD to
clarify that, for eddy current (NDT) inspections performed after the
effective date of this AD, accomplishment of a detailed inspection for
corrosion must be done at the same time as the eddy current inspection.
Clarification of Actions in AD 90-03-08
In paragraphs D.1.a. and E.1. of AD 90-03-08 we specify doing
initial and repetitive X-ray inspections for cracking of the rim area
of the rear pressure bulkhead as a separate action. Upon further review
of Airbus Service Bulletin A300-53-218, Revision 1, we have determined
that these inspections are related investigative actions to the eddy
current inspections specified in paragraphs D.1.c. and E.3 of AD 90-03-
08. Paragraph 3.B. (4) of Revision 02 of Airbus Service Bulletin A300-
53-0218 describes these inspections in the same manner. Therefore, we
have removed the X-ray inspection specified in the existing AD and
added paragraph (l) to this proposed AD to ensure that this inspection
is done, if necessary, depending on the results of the inspections
specified in paragraphs (f)(2) and (h)(2) of this AD (specified as
paragraphs D.1c. and E.3 of AD 90-03-08).
Revision 02 of Airbus Service Bulletin A300-53-0218 removes MSN 002
from the inspection of the area between STGR 25 LH and RH and removes
MSNs 009 through 018 from the inspection of the area between STGR 26 LH
and RH. We have revised paragraphs (f)(2)(i) and (f)(2)(ii)
accordingly.
Changes to Existing AD
This proposed AD would retain certain requirements of AD 90-03-08.
Since AD 90-03-08 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a
[[Page 43388]]
result, the corresponding paragraph identifiers have changed in this
proposed AD, as listed in the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 90-03-08 this proposed AD
------------------------------------------------------------------------
Paragraph D............................... Paragraphs (f) and (g).
Paragraph E............................... Paragraph (h).
Paragraph F............................... Paragraph (n).
------------------------------------------------------------------------
Explanation of Change to Applicability
We have changed the airplane model designations in the
applicability of this proposed AD to be consistent with the parallel
French airworthiness directive.
Explanation of Change Made to Existing Requirements
Where the service bulletin specifies to ``visually inspect,''
except for the inspection for missing or damaged sealant, and where AD
90-03-08 specifies to do a ``visual inspection,'' we specify to do a
``detailed inspection'' in this proposed AD. We have included the
definition for a detailed inspection in Note 1 of this proposed AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average U.S.-
Action Work hours labor rate Cost per airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections (required by AD 90-03-08) 10 $80 $800, per inspection 51 $40,800, per inspection cycle.
cycle.
New Inspections (required by this AD) 10 80 800, per inspection 51 $40,800, per inspection cycle.
cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-6481 (55 FR 1799, January 19, 1990) and adding
the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2006-25423; Directorate Identifier 2006-NM-
029-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by August
31, 2006.
Affected ADs
(b) This AD supersedes AD 90-03-08.
Applicability
(c) This AD applies to all Airbus Model A300 airplanes,
certificated in any category; except the following airplanes:
(1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes;
(2) Model A300 B4-605R and B4-622R airplanes;
(3) Model A300 F4-605R and F4-622R airplanes; and
(4) Airbus Model A300 C4-605R Variant F airplanes.
Unsafe Condition
(d) This AD results from reports of corrosion and cracking in
the various components associated with the rear pressure bulkhead.
We are issuing this AD to prevent reduced structural capability of
the fuselage and consequent decompression of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD 90-03-08 With New Repetitive
Intervals
Initial Inspections
(f) Within the time limits specified in paragraph (g) of this
AD, conduct the inspections specified in paragraphs (f)(1) through
(f)(4) of this AD in accordance with Airbus Service Bulletin
[[Page 43389]]
A300-53-218, Revision 1, dated July 28, 1989; or Airbus Service
Bulletin A300-53-0218, Revision 02, dated May 10, 2005. After the
effective date of this AD, Airbus Service Bulletin A300-53-0218,
Revision 02, dated May 10, 2005, must be used.
(1) Perform a detailed inspection for corrosion and cracking of
the upper rim area of the rear pressure bulkhead from the aft face.
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.''
(2) Perform an eddy current inspection for cracks from the
outboard side in the applicable areas specified in paragraph
(f)(2)(i) or (f)(2)(ii) of this AD.
(i) For airplanes, manufacturer's serial number (MSN) 003
through 008: Between Stringer (STGR) 25 left hand (LH) and right
hand (RH).
(ii) For airplanes, MSN 019 through 305: Between STGR 26 LH and
RH.
(3) Perform a detailed inspection for cracks and corrosion of
the service apertures in the rear pressure bulkhead.
(4) Perform an eddy current inspection for cracks of the
apertures for the auxiliary power unit (APU) bleed-air and fuel.
(g) At the applicable time specified in paragraph (g)(1) or
(g)(2) of this AD, do the inspections required by paragraph (f) of
this AD.
(1) For airplanes having accumulated 26,000 landings or fewer as
of February 23, 1990 (the effective date of AD 90-03-08): Perform
the initial inspections required by paragraph (f) of this AD, prior
to the accumulation of 24,000 landings or within 2,000 landings
after February 23, 1990, whichever occurs later.
(2) For airplanes having accumulated more than 26,000 landings
as of February 23, 1990: Perform the initial inspections required by
paragraph (f) of this AD, within 1,000 landings after February 23,
1990.
Repetitive Inspections
(h) If no cracking or corrosion is found during the inspections
required by paragraph (f) of this AD, repeat the inspections
specified in paragraphs (h)(1), (h)(2), (h)(3), (h)(4), and (h)(5)
of this AD thereafter at the times specified in the paragraphs.
(1) Repeat the detailed inspections of the upper rim area
specified in paragraph (f)(1) of this AD thereafter at intervals not
to exceed 8,000 landings.
(2) Repeat the eddy current inspection from the outboard side
between STGR 25 LH and RH, or STGR 26 LH and RH, as applicable,
specified in paragraph (f)(2) of this AD thereafter at intervals not
to exceed 8,000 landings.
(3) Repeat the detailed inspection of the service apertures
specified in paragraph (f)(3) of this AD thereafter at intervals not
to exceed 6,000 landings.
(4) Repeat eddy current inspections of APU fuel apertures
specified in paragraph (f)(4) of this AD thereafter at intervals not
to exceed 6,000 landings.
(5) At the earlier of the times specified in paragraph (g)(5)(i)
and (g)(5)(ii) of this AD, do the eddy current inspection of the APU
bleed-air line service aperture specified in paragraph (f)(4) of
this AD. Repeat the inspection thereafter at intervals not to exceed
6,000 landing.
(i) Within 12,000 landings since the last inspection of the APU
bleed-air line service aperture specified in paragraph (f)(4) of
this AD.
(ii) Within 6,000 landings since the last inspection of the APU
bleed-air line service aperture specified in paragraph (f)(4) of
this AD or within 2,000 landings after the effective date of this
AD, whichever occurs later.
New Requirements of This AD
Inspection for Sealant and Corrective Action
(i) Within the time limits specified in paragraph (j) of this
AD: Do a general visual inspection of the area between the outer
attachment angle and circumferential joint doubler to determine if
sealant is missing or damaged and do all applicable corrective
actions in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A300-53-0218, Revision 02, dated May 10, 2005. Do
all applicable corrective actions before further flight. Repeat the
inspection thereafter at intervals not to exceed 6,000 landings.
Note 2: 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.''
(j) At the applicable time specified in paragraph (j)(1) or
(j)(2) of this AD, do the inspections required by paragraph (i) of
this AD.
(1) For airplanes having accumulated 26,000 landings or fewer as
of the effective date of this AD): Perform the initial inspection
required by paragraph (i) of this AD, prior to the accumulation of
24,000 landings or within 2,000 landings after the effective date of
this AD, whichever occurs later.
(2) For airplanes having accumulated more than 26,000 landings
as of the effective date of this AD: Perform the initial inspection
required by paragraph (i) of this AD, within 1,000 landings after
the effective date of this AD.
Additional Inspections
(k) For airplanes on which the inspections specified in
paragraphs (f)(2), (f)(4), (h)(2), and (h)(4) of this AD are
accomplished after the effective date of this AD: Where this AD
requires an eddy current inspection for cracks, do a detailed
inspection for corrosion at the same time as the eddy current
inspection for cracks in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0218, Revision 02,
dated May 10, 2005.
(l) For airplanes on which the inspections specified in
paragraphs (f)(2) and (h)(2) of this AD are accomplished after the
effective date of this AD: If any crack is found during any
inspection required by paragraph (f)(2) or (h)(2), before further
flight, do an X-ray inspection for cracking of the rim area of the
rear pressure bulkhead in the area of STGR 21 LH and RH in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-0218, Revision 02, dated May 10, 2005.
New Repetitive Inspections
(m) For airplanes on which a repair has been done in accordance
with Airbus Service Bulletin A300-53-218, Revision 1, dated July 28,
1989; or Airbus Service Bulletin A300-53-0218, Revision 02, dated
May 10, 2005; before the effective date of this AD: At the later of
the times specified in paragraphs (m)(1) and (m)(2) of this AD, do
the inspections specified in paragraphs (h), (k), and (l) of this
AD. Repeat the inspections specified in paragraphs (h), (k), and (l)
of this AD thereafter at the applicable times specified in paragraph
(h).
(1) Within the times specified in paragraph (h) of this AD.
(2) Within 2,000 landings after the effective date of this AD.
[[Page 43390]]
Corrective Actions for Cracking and Corrosion and Repetitive
Inspections
(n) If cracking or corrosion is found during any inspection
required by paragraph (f), (h), (k), (l) or (m) of this AD, repair
prior to further flight, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-218, Revision 1,
dated July 28, 1989; or Airbus Service Bulletin A300-53-0218,
Revision 02, dated May 10, 2005. As of the effective date of this
AD, do the repair in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-53-0218, Revision 02, dated May 10,
2005; except where the service bulletin specifies to contact the
manufacturer to repair certain conditions, this AD requires
repairing those conditions using a method approved by either the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or
its delegated agent). As of the effective date of this AD, repeat
the inspections specified in paragraphs (h), (k), and (l) of this AD
thereafter at the applicable times specified in paragraph (h).
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 90-03-08 are
not approved as AMOCs with this AD.
Related Information
French airworthiness directive F-2005-093 R1, dated August 3,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on July 21, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-12301 Filed 7-31-06; 8:45 am]
BILLING CODE 4910-13-P
