Airworthiness Directives; Airbus Model A310 Series Airplanes, 50250-50253 [E8-19715]
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Federal Register / Vol. 73, No. 166 / Tuesday, August 26, 2008 / Proposed Rules
Model Avro 146–RJ70A, 146–RJ85A, and
146–RJ100A airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from issuance of a later
revision to the airworthiness limitations of
the BAe/Avro 146 Aircraft Maintenance
Manual (AMM), which specifies new
inspections and compliance times for
inspection and replacement actions. We are
issuing this AD to ensure that fatigue
cracking of certain structural elements is
detected and corrected; such fatigue cracking
could adversely affect the structural integrity
of these airplanes.
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.
Certain Requirements of AD 2005–23–12
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance (AMOC)
according to paragraph (i) of this AD. The
request should include a description of
changes to the required inspections that will
ensure the continued operational safety of
the airplane.
Airworthiness Limitations Revision
(f) Within 30 days after December 27, 2005
(the effective date of AD 2005–23–12), revise
the Airworthiness Limitations Section (ALS)
of the Instructions for Continued
Airworthiness to incorporate new and more
restrictive life limits for certain items and
new and more restrictive inspections to
detect fatigue cracking in certain structures,
in accordance with a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the Civil Aviation Authority (or its delegated
agent). Section 05–10–01, dated July 15,
2005, of Chapter 5 of the BAe/Avro 146
Aircraft Maintenance Manual is one
approved method. This section references
other sections of the AMM. The applicable
revision level of the referenced sections is the
revision level that is in effect on December
27, 2005.
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New Requirements of This AD
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Alternative Methods of Compliance
(AMOCs)
(i) The Manager, International Branch,
ANM=116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Todd Thompson, Aerospace
Engineer, International Branch, ANM–116,
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–4056; telephone (425) 227–1175; fax
(425) 227–1149. Before using any approved
AMOC on any airplane to which the AMOC
applies, notify your appropriate principal
inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your
local FSDO.
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Notice of proposed rulemaking
(NPRM).
ACTION:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Airbus
Model A310 series airplanes. The
existing AD currently requires repetitive
detailed inspections to detect cracks
propagating from the fastener holes that
attach the left- and right-hand pick-up
angles at frame 40 to the wing lower
skin and fuselage panel, and corrective
actions, if necessary. This proposed AD
would revise the intervals for
accomplishing the repetitive detailed
inspections and would provide for an
optional terminating modification for
the repetitive inspections. This
proposed AD results from mandatory
continuing airworthiness information
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. We are proposing this AD to
prevent reduced structural integrity of
the airplane due to fatigue damage and
consequent cracking of the pick-up
angles at frame 40.
DATES: We must receive comments on
this proposed AD by September 25,
2008.
DEPARTMENT OF TRANSPORTATION
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
Federal Aviation Administration
Examining the AD Docket
Related Information
(j) The European Aviation Safety Agency
airworthiness directive 2007–0271, dated
October 16, 2007, also addresses the subject
of this AD.
Issued in Renton, Washington, on August
18, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–19714 Filed 8–25–08; 8:45 am]
BILLING CODE 4910–13–P
14 CFR Part 39
Later Revision for Airworthiness Limitations
(g) Within 30 days after the effective date
of this AD, revise the ALS of the Instructions
for Continued Airworthiness to incorporate
new and more restrictive life limits for
certain items and new and more restrictive
inspections to detect fatigue cracking in
certain structures, in accordance with a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
VerDate Aug<31>2005
Aviation Safety Agency (or its delegated
agent). Sections 05–10 and 05–20, both dated
August 15, 2007, of Chapter 5 of the BAe/
Avro 146 Aircraft Maintenance Manual is
one approved method. Those sections
reference other sections of the AMM. The
applicable revision level of the referenced
sections is the revision level that is in effect
on the effective date of this AD. Incorporating
the new and more restrictive life limits and
inspections into the ALS terminates the
requirements of paragraphs (f) and (g) of this
AD, and after incorporation has been done,
the limitations required by paragraph (f) of
this AD may be removed from the ALS.
(h) Except as specified in paragraph (i) of
this AD: After the actions specified in
paragraph (f) or (g) of this AD have been
accomplished, no alternative inspections or
inspection intervals may be approved for the
structural elements specified in the
documents listed in paragraph (f) or (g) of
this AD.
[Docket No. FAA–2008–0908; Directorate
Identifier 2007–NM–190–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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ADDRESSES:
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
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Federal Register / Vol. 73, No. 166 / Tuesday, August 26, 2008 / Proposed Rules
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0908; Directorate Identifier
2007–NM–190–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On December 22, 2000, we issued AD
2000–26–14, amendment 39–12064 (66
FR 1031, January 5, 2001), for all Airbus
Model A310 series airplanes. That AD
requires repetitive detailed visual
inspections to detect cracks propagating
from the fastener holes that attach the
left- and right-hand pick-up angles at
frame 40 to the wing lower skin and
fuselage panel, and corrective actions, if
necessary. That AD resulted from a
report indicating that structural damage
was found on the pick-up angles at the
junction between the wing lower surface
and the fuselage skin at frame 40. We
issued that AD to prevent reduced
structural integrity of the airplane due
to fatigue damage and consequent
cracking of the pick-up angles at frame
40.
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Actions Since Existing AD Was Issued
Since we issued AD 2000–26–14,
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has informed us that, as a
result of A310 extended service goal
activities, the thresholds and repetitive
intervals for the existing repetitive
detailed visual inspections required by
AD 2000–26–14 must be modified to
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18:09 Aug 25, 2008
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adequately address the identified unsafe
condition.
Relevant Service Information
Airbus has issued Revision 03 of
Service Bulletin A310–53–2111, dated
May 21, 2007 (AD 2000–26–14 refers to
Airbus Service Bulletin A310–53–2111,
Revision 01, dated June 21, 2000, as the
appropriate source of service
information for accomplishing the
required actions). The inspection
procedures specified in Revision 03 are
essentially identical to those specified
in Revision 01. Revision 03 revises the
thresholds and repetitive intervals for
the inspections and thresholds for
replacing pick-up angles. No additional
work is required by Revision 03 for
airplanes inspected in accordance with
earlier revisions. Accomplishing the
actions specified in the service
information is intended to adequately
address the unsafe condition. The EASA
mandated Service Bulletin A310–53–
2111, Revision 03, and issued
airworthiness directive 2007–0184,
dated July 3, 2007, to ensure the
continued airworthiness of these
airplanes in the European Union.
Airbus also issued Service Bulletin
A310–53–2119, Revision 01, dated
February 27, 2007. The service bulletin
describes procedures for removing the
existing pick-up angles and installing a
reinforced doubler between frames (FR)
FR40 and FR41, and doing applicable
related investigative and corrective
actions. The related investigative
actions include inspecting the diameters
of the holes, and doing a rotating probe
inspection of the holes 1 through 70.
The corrective actions involve
contacting the airplane manufacturer for
repair procedures. EASA airworthiness
directive 2007–0184 refers to this
service bulletin as an optional
terminating action for the repetitive
inspections specified in Service Bulletin
A310–53–2111, Revision 03.
FAA’s Determination and Requirements
of the Proposed AD
These airplanes are manufactured in
France and are type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. As described
in FAA Order 8100.14A, ‘‘Interim
Procedures for Working with the
European Community on Airworthiness
Certification and Continued
Airworthiness,’’ dated August 12, 2005,
the EASA has kept the FAA informed of
the situation described above. We have
examined the EASA’s findings,
evaluated all pertinent information, and
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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 2000–26–14 and would continue to
require repetitive detailed inspections to
detect cracks propagating from the
fasteners holes that attach the left- and
right-hand pick-up angles at frame 40 to
the wing lower skin and fuselage panel,
and corrective actions, if necessary. This
proposed AD would revise the intervals
for accomplishing the repetitive detailed
inspections and would provide for an
optional terminating modification for
the repetitive inspections.
Change to Existing AD
This proposed AD would retain all
requirements of AD 2000–26–14. Since
AD 2000–26–14 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2000–26–14
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
(a) .......................
(b) .......................
(c) .......................
(d) .......................
(e) .......................
(f) ........................
Corresponding
requirement in
this proposed
AD
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
(f).
(g).
(h).
(i).
(j).
(k).
We also have changed all references
to a ‘‘detailed visual inspection’’ in the
existing AD to ‘‘detailed inspection’’ in
this action.
Costs of Compliance
This proposed AD would affect about
68 Model A310 series airplanes of U.S.
registry.
The inspections that are required by
AD 2000–26–14 and retained in this
proposed AD take about 2 work hours
per airplane, at an average labor rate of
$80 per work hour. Based on these
figures, the estimated cost of the
currently required actions is $10,880, or
$160 per airplane, per inspection cycle.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
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Federal Register / Vol. 73, No. 166 / Tuesday, August 26, 2008 / Proposed Rules
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.
Airbus: Docket No. FAA–2008–0908;
Directorate Identifier 2007–NM–190–AD.
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.
Unsafe Condition
(d) This AD results from mandatory
continuing airworthiness information
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. We are
issuing this AD to prevent reduced structural
integrity of the airplane due to fatigue
damage and consequent cracking of the pickup angles at frame 40.
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:
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–12064 (66
FR 1031, January 5, 2001) and adding
the following new airworthiness
directive (AD):
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18:09 Aug 25, 2008
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Comments Due Date
(a) The FAA must receive comments on
this AD action by September 25, 2008.
Affected ADs
(b) This AD supersedes AD 2000–26–14.
Applicability
(c) This AD applies to Airbus Model A310
series airplanes, certificated in any category,
except those airplanes modified in-service in
accordance with Airbus Service Bulletin
A310–53–2119, dated October 25, 2005; or
Revision 01, dated February 27, 2007.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Requirements of AD 2000–26–14
Inspections and Corrective Actions
(f) Perform a detailed inspection to detect
cracks propagating from the fastener holes
that attach the left- and right-hand pick-up
angles at frame 40 to the wing lower skin and
fuselage panel, at the time specified in
paragraph (g), (h), (i), (j) or (k) of this AD, as
applicable. Perform the actions in accordance
with Figure 2, Sheet 1, ‘‘Synoptic Chart,’’ of
Airbus Service Bulletin A310–53A2111,
Revision 01, dated June 21, 2000, except as
provided by paragraph (l) of this AD.
(1) If no cracking is found during the
inspection required by paragraph (f) of this
AD, repeat the detailed inspection thereafter
at the interval specified in paragraph (f)(1)(i)
or (f)(1)(ii) of this AD, as applicable, except
as provided by paragraph (n) of this AD.
(i) For Model A310–200 series airplanes:
Except as provided by paragraph (i) of this
AD, repeat the inspection thereafter at
intervals not to exceed 1,000 flight cycles or
2,600 flight hours, whichever occurs first.
(ii) For Model A310–300 series airplanes:
Except as provided by paragraphs (i) of this
AD, repeat the inspection thereafter at
intervals not to exceed 850 flight cycles or
2,800 flight hours, whichever occurs first.
(2) If any cracking is found during the
inspection required by paragraph (f) of this
AD, prior to further flight, perform applicable
corrective actions (including repair (drilling
and reaming a crack stop hole in the pickup angle, performing a Rototest inspection
and repetitive detailed inspections at the
time specified in the service bulletin, and
replacing the pick-up angle with a new angle
at the time specified in the service bulletin,
except as provided by paragraph (o) of this
AD); or immediate replacement of any
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cracked angle with a new angle). Perform the
actions and repetitive inspections in
accordance with Figure 2, Sheet 1, ‘‘Synoptic
Chart,’’ of Airbus Service Bulletin A310–
53A2111, Revision 01, dated June 21, 2000,
except as provided by paragraph (l) of this
AD.
Note 1: Accomplishment of the actions
required by paragraph (f) of this AD in
accordance with Airbus Service Bulletin
A310–53A2111, dated April 21, 2000, is
considered to be acceptable for compliance
with the requirements of that paragraph.
Compliance Times
(g) For Model A310–200 series airplanes:
Except as provided by paragraphs (i), (j), and
(k) of this AD, perform the initial inspection
at the later of the times specified in
paragraphs (g)(1) and (g)(2) of this AD.
(1) Prior to the accumulation of 7,900 total
flight cycles or 23,600 total flight hours,
whichever occurs first.
(2) Within 700 flight cycles or 1,200 flight
hours after February 9, 2001 (the effective
date of AD 2000–26–14), whichever occurs
first.
(h) For Model A310–300 series airplanes:
Except as provided by paragraphs (i), (j), and
(k) of this AD, perform the initial inspection
required by paragraph (f) of this AD at the
later of the times specified in paragraphs
(h)(1) and (h)(2) of this AD.
(1) Prior to the accumulation of 6,700 total
flight cycles or 24,700 total flight hours,
whichever occurs first.
(2) Within 700 flight cycles or 1,200 flight
hours after February 9, 2001, whichever
occurs first.
(i) For airplanes that have accumulated
more than 18,000 total flight cycles or 53,000
total flight hours as of February 9, 2001:
Perform the initial inspection required by
paragraph (f) of this AD within 350 flight
cycles or 600 flight hours after February 9,
2001, whichever occurs first. Repeat the
inspection thereafter at intervals not to
exceed 350 flight cycles or 600 flight hours,
whichever occurs first.
(j) For airplanes having manufacturer’s
serial number 0162 through 0326 inclusive,
on which Airbus Service Bulletin A310–53–
2014 has been accomplished prior to
February 9, 2001: The initial inspection
threshold may be counted from the date of
accomplishment of Airbus Service Bulletin
A310–53–2014.
(k) For airplanes on which a pick-up angle
has been replaced: For that pick-up angle
only, the initial inspection threshold may be
counted from the date of installation of the
new pick-up angle.
Note 2: For the purposes of this AD, a
detailed inspection is defined as: ‘‘An
intensive visual examination of a specific
structural area, system, installation, or
assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.’’
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Federal Register / Vol. 73, No. 166 / Tuesday, August 26, 2008 / Proposed Rules
New Requirements of This AD
New Revisions of Service Bulletin
(l) As of the effective date of this AD, use
only the Accomplishment Instructions of
Airbus Service Bulletin A310–53–2111,
Revision 03, dated May 21, 2007, to do the
inspections and corrective actions required
by paragraph (f) of this AD; except where
Figure 2 Sheet 2 of the service bulletin
specifies actions for crack length of ‘‘<54 mm
(2.126 in.)’’ and ‘‘<69 mm (2.716 in.),’’ this
AD requires the corresponding actions for
crack lengths less than or equal to those
measurements.
(m) Inspections and applicable corrective
actions done before the effective date of this
AD in accordance with Airbus Service
Bulletin A310–53–2111, Revision 02, dated
October 25, 2005, are acceptable for
compliance with the requirements of
paragraph (f) of this AD.
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Revised Repetitive Intervals for Detailed
Inspections
(n) As of the effective date of this AD,
repeat the detailed inspections for no crack
findings required by paragraph (f)(1)(i),
(f)(1)(ii), or (i) of this AD, as applicable, at the
applicable times specified in Table 1 of this
AD, until the modification specified in
paragraph (p) of this AD is done.
TABLE 1—REVISED REPETITIVE INTERVALS FOR CERTAIN DETAILED INSPECTIONS
For model—
Repeat the inspection at the later of the
following times—
Repeat the inspection at the later of the
following times—
And thereafter at intervals not
to exceed—
(1) A310–200 series
airplanes.
Within 950 flight cycles or 1,900 flight
hours since the last inspection required
by paragraph (f)(1)(ii) or (i) of this AD,
whichever occurs first.
Within 900 flight cycles or 2,550 flight
hours since the last inspection required
by paragraph (f)(1)(ii) or (i) of this AD,
whichever occurs first.
Within 800 flight cycles or 4,000 flight
hours since the last inspection required
by paragraph (f)(1)(ii) or (i) of this AD,
whichever occurs first.
Within 50 flight cycles or 250 flight hours
after the effective date of this AD,
whichever occurs first.
950 flight cycles or 1,900 flight
hours, whichever occurs first.
Within 50 flight cycles or 250 flight hours
after the effective date of this AD,
whichever occurs first.
900 flight cycles or 2,550 flight
hours, whichever occurs first.
Within 50 flight cycles or 250 flight hours
after the effective date of this AD,
whichever occurs first.
800 flight cycles or 4,000 flight
hours, whichever occurs first.
(2) A310–300 series
airplanes (short
range).
(3) A310–300 series
airplanes (long
range).
Revised Threshold for Replacing the PickUp Angles
(o) As of the effective date of this AD, do
the replacement of the pick-up angle required
by paragraph (f)(2) of this AD, at the
applicable time specified in Table 2 of this
AD.
TABLE 2—REVISED THRESHOLDS FOR REPLACING PICK-UP ANGLES
For model—
Replace at the earlier of the following times—
(1) A310–200 series airplanes.
At the time specified in paragraph (f)(2) of this
AD for replacing the pick-up angle.
(2) A310–300 series airplanes (short range).
At the time specified in paragraph (f)(2) of this
AD for replacing the pick-up angle.
(3) A310–300 series airplanes (long range).
At the time specified in paragraph (f)(2) of this
AD for replacing the pick-up angle.
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Optional Terminating Modification
(p) Remove the existing pick-up angles and
install a reinforced doubler between frames
(FR) FR40 and FR41, and perform applicable
related investigative and corrective actions
by accomplishing all the applicable actions
specified in the Accomplishment
Instructions of Airbus Service Bulletin A310–
53–2119, Revision 01, dated February 27,
2007; except as provided by paragraph (q) of
this AD. Accomplishing these actions ends
the repetitive inspections required by this
AD.
(q) If any crack is detected and Airbus
Service Bulletin A310–53–2119, Revision 01,
dated February 27, 2007, specifies to contact
Airbus: Before further flight, repair the crack
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).
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18:09 Aug 25, 2008
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Within 1,500 flight cycles or 3,000 flight hours since the last detailed
inspection, or within 30 days after the effective date of this AD,
whichever occurs later.
Within 1,600 flight cycles or 4,600 flight hours since the last detailed
inspection, or within 30 days after the effective date of this AD,
whichever occurs later.
Within 1,400 flight cycles or 7,200 flight hours since the last detailed
inspection, or within 30 days after the effective date of this AD,
whichever occurs later.
(r) Actions done before the effective date of
this AD in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–53–2119, dated
October 25, 2005, are acceptable for
compliance with the corresponding
requirements of paragraph (p) of this AD.
Alternative Methods of Compliance
(AMOCs)
(s) The Manager, International Branch,
ANM–116, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send
information to ATTN: Dan Rodina,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2125; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
Related Information
(t) EASA airworthiness directive 2007–
0184, dated July 3, 2007, also addresses the
subject of this AD.
Issued in Renton, Washington, on August
18, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–19715 Filed 8–25–08; 8:45 am]
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]]>Agencies
[Federal Register Volume 73, Number 166 (Tuesday, August 26, 2008)]
[Proposed Rules]
[Pages 50250-50253]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-19715]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0908; Directorate Identifier 2007-NM-190-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series 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 A310 series airplanes.
The existing AD currently requires repetitive detailed inspections to
detect cracks propagating from the fastener holes that attach the left-
and right-hand pick-up angles at frame 40 to the wing lower skin and
fuselage panel, and corrective actions, if necessary. This proposed AD
would revise the intervals for accomplishing the repetitive detailed
inspections and would provide for an optional terminating modification
for the repetitive inspections. This proposed AD results from mandatory
continuing airworthiness information originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. We are proposing this AD to prevent
reduced structural integrity of the airplane due to fatigue damage and
consequent cracking of the pick-up angles at frame 40.
DATES: We must receive comments on this proposed AD by September 25,
2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be
[[Page 50251]]
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Dan Rodina, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0908;
Directorate Identifier 2007-NM-190-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On December 22, 2000, we issued AD 2000-26-14, amendment 39-12064
(66 FR 1031, January 5, 2001), for all Airbus Model A310 series
airplanes. That AD requires repetitive detailed visual inspections to
detect cracks propagating from the fastener holes that attach the left-
and right-hand pick-up angles at frame 40 to the wing lower skin and
fuselage panel, and corrective actions, if necessary. That AD resulted
from a report indicating that structural damage was found on the pick-
up angles at the junction between the wing lower surface and the
fuselage skin at frame 40. We issued that AD to prevent reduced
structural integrity of the airplane due to fatigue damage and
consequent cracking of the pick-up angles at frame 40.
Actions Since Existing AD Was Issued
Since we issued AD 2000-26-14, European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has informed us that, as a result of A310 extended
service goal activities, the thresholds and repetitive intervals for
the existing repetitive detailed visual inspections required by AD
2000-26-14 must be modified to adequately address the identified unsafe
condition.
Relevant Service Information
Airbus has issued Revision 03 of Service Bulletin A310-53-2111,
dated May 21, 2007 (AD 2000-26-14 refers to Airbus Service Bulletin
A310-53-2111, Revision 01, dated June 21, 2000, as the appropriate
source of service information for accomplishing the required actions).
The inspection procedures specified in Revision 03 are essentially
identical to those specified in Revision 01. Revision 03 revises the
thresholds and repetitive intervals for the inspections and thresholds
for replacing pick-up angles. No additional work is required by
Revision 03 for airplanes inspected in accordance with earlier
revisions. Accomplishing the actions specified in the service
information is intended to adequately address the unsafe condition. The
EASA mandated Service Bulletin A310-53-2111, Revision 03, and issued
airworthiness directive 2007-0184, dated July 3, 2007, to ensure the
continued airworthiness of these airplanes in the European Union.
Airbus also issued Service Bulletin A310-53-2119, Revision 01,
dated February 27, 2007. The service bulletin describes procedures for
removing the existing pick-up angles and installing a reinforced
doubler between frames (FR) FR40 and FR41, and doing applicable related
investigative and corrective actions. The related investigative actions
include inspecting the diameters of the holes, and doing a rotating
probe inspection of the holes 1 through 70. The corrective actions
involve contacting the airplane manufacturer for repair procedures.
EASA airworthiness directive 2007-0184 refers to this service bulletin
as an optional terminating action for the repetitive inspections
specified in Service Bulletin A310-53-2111, Revision 03.
FAA's Determination and Requirements of the Proposed AD
These airplanes are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, the EASA has kept the FAA informed of the
situation described above. We have examined the EASA'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 2000-26-14 and would continue
to require repetitive detailed inspections to detect cracks propagating
from the fasteners holes that attach the left- and right-hand pick-up
angles at frame 40 to the wing lower skin and fuselage panel, and
corrective actions, if necessary. This proposed AD would revise the
intervals for accomplishing the repetitive detailed inspections and
would provide for an optional terminating modification for the
repetitive inspections.
Change to Existing AD
This proposed AD would retain all requirements of AD 2000-26-14.
Since AD 2000-26-14 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a 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 2000-26-14 this proposed AD
------------------------------------------------------------------------
paragraph (a)........................... paragraph (f).
paragraph (b)........................... paragraph (g).
paragraph (c)........................... paragraph (h).
paragraph (d)........................... paragraph (i).
paragraph (e)........................... paragraph (j).
paragraph (f)........................... paragraph (k).
------------------------------------------------------------------------
We also have changed all references to a ``detailed visual
inspection'' in the existing AD to ``detailed inspection'' in this
action.
Costs of Compliance
This proposed AD would affect about 68 Model A310 series airplanes
of U.S. registry.
The inspections that are required by AD 2000-26-14 and retained in
this proposed AD take about 2 work hours per airplane, at an average
labor rate of $80 per work hour. Based on these figures, the estimated
cost of the currently required actions is $10,880, or $160 per
airplane, per inspection cycle.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
[[Page 50252]]
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 39-12064 (66 FR 1031, January 5, 2001) and adding
the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2008-0908; Directorate Identifier 2007-NM-
190-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by September
25, 2008.
Affected ADs
(b) This AD supersedes AD 2000-26-14.
Applicability
(c) This AD applies to Airbus Model A310 series airplanes,
certificated in any category, except those airplanes modified in-
service in accordance with Airbus Service Bulletin A310-53-2119,
dated October 25, 2005; or Revision 01, dated February 27, 2007.
Unsafe Condition
(d) This AD results from mandatory continuing airworthiness
information originated by an aviation authority of another country
to identify and correct an unsafe condition on an aviation product.
We are issuing this AD to prevent reduced structural integrity of
the airplane due to fatigue damage and consequent cracking of the
pick-up angles at frame 40.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Requirements of AD 2000-26-14
Inspections and Corrective Actions
(f) Perform a detailed inspection to detect cracks propagating
from the fastener holes that attach the left- and right-hand pick-up
angles at frame 40 to the wing lower skin and fuselage panel, at the
time specified in paragraph (g), (h), (i), (j) or (k) of this AD, as
applicable. Perform the actions in accordance with Figure 2, Sheet
1, ``Synoptic Chart,'' of Airbus Service Bulletin A310-53A2111,
Revision 01, dated June 21, 2000, except as provided by paragraph
(l) of this AD.
(1) If no cracking is found during the inspection required by
paragraph (f) of this AD, repeat the detailed inspection thereafter
at the interval specified in paragraph (f)(1)(i) or (f)(1)(ii) of
this AD, as applicable, except as provided by paragraph (n) of this
AD.
(i) For Model A310-200 series airplanes: Except as provided by
paragraph (i) of this AD, repeat the inspection thereafter at
intervals not to exceed 1,000 flight cycles or 2,600 flight hours,
whichever occurs first.
(ii) For Model A310-300 series airplanes: Except as provided by
paragraphs (i) of this AD, repeat the inspection thereafter at
intervals not to exceed 850 flight cycles or 2,800 flight hours,
whichever occurs first.
(2) If any cracking is found during the inspection required by
paragraph (f) of this AD, prior to further flight, perform
applicable corrective actions (including repair (drilling and
reaming a crack stop hole in the pick-up angle, performing a
Rototest inspection and repetitive detailed inspections at the time
specified in the service bulletin, and replacing the pick-up angle
with a new angle at the time specified in the service bulletin,
except as provided by paragraph (o) of this AD); or immediate
replacement of any cracked angle with a new angle). Perform the
actions and repetitive inspections in accordance with Figure 2,
Sheet 1, ``Synoptic Chart,'' of Airbus Service Bulletin A310-
53A2111, Revision 01, dated June 21, 2000, except as provided by
paragraph (l) of this AD.
Note 1: Accomplishment of the actions required by paragraph (f)
of this AD in accordance with Airbus Service Bulletin A310-53A2111,
dated April 21, 2000, is considered to be acceptable for compliance
with the requirements of that paragraph.
Compliance Times
(g) For Model A310-200 series airplanes: Except as provided by
paragraphs (i), (j), and (k) of this AD, perform the initial
inspection at the later of the times specified in paragraphs (g)(1)
and (g)(2) of this AD.
(1) Prior to the accumulation of 7,900 total flight cycles or
23,600 total flight hours, whichever occurs first.
(2) Within 700 flight cycles or 1,200 flight hours after
February 9, 2001 (the effective date of AD 2000-26-14), whichever
occurs first.
(h) For Model A310-300 series airplanes: Except as provided by
paragraphs (i), (j), and (k) of this AD, perform the initial
inspection required by paragraph (f) of this AD at the later of the
times specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Prior to the accumulation of 6,700 total flight cycles or
24,700 total flight hours, whichever occurs first.
(2) Within 700 flight cycles or 1,200 flight hours after
February 9, 2001, whichever occurs first.
(i) For airplanes that have accumulated more than 18,000 total
flight cycles or 53,000 total flight hours as of February 9, 2001:
Perform the initial inspection required by paragraph (f) of this AD
within 350 flight cycles or 600 flight hours after February 9, 2001,
whichever occurs first. Repeat the inspection thereafter at
intervals not to exceed 350 flight cycles or 600 flight hours,
whichever occurs first.
(j) For airplanes having manufacturer's serial number 0162
through 0326 inclusive, on which Airbus Service Bulletin A310-53-
2014 has been accomplished prior to February 9, 2001: The initial
inspection threshold may be counted from the date of accomplishment
of Airbus Service Bulletin A310-53-2014.
(k) For airplanes on which a pick-up angle has been replaced:
For that pick-up angle only, the initial inspection threshold may be
counted from the date of installation of the new pick-up angle.
Note 2: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
[[Page 50253]]
New Requirements of This AD
New Revisions of Service Bulletin
(l) As of the effective date of this AD, use only the
Accomplishment Instructions of Airbus Service Bulletin A310-53-2111,
Revision 03, dated May 21, 2007, to do the inspections and
corrective actions required by paragraph (f) of this AD; except
where Figure 2 Sheet 2 of the service bulletin specifies actions for
crack length of ``<54 mm (2.126 in.)'' and ``<69 mm (2.716 in.),''
this AD requires the corresponding actions for crack lengths less
than or equal to those measurements.
(m) Inspections and applicable corrective actions done before
the effective date of this AD in accordance with Airbus Service
Bulletin A310-53-2111, Revision 02, dated October 25, 2005, are
acceptable for compliance with the requirements of paragraph (f) of
this AD.
Revised Repetitive Intervals for Detailed Inspections
(n) As of the effective date of this AD, repeat the detailed
inspections for no crack findings required by paragraph (f)(1)(i),
(f)(1)(ii), or (i) of this AD, as applicable, at the applicable
times specified in Table 1 of this AD, until the modification
specified in paragraph (p) of this AD is done.
Table 1--Revised Repetitive Intervals for Certain Detailed Inspections
----------------------------------------------------------------------------------------------------------------
Repeat the inspection at Repeat the inspection at And thereafter at
For model-- the later of the following the later of the following intervals not to
times-- times-- exceed--
----------------------------------------------------------------------------------------------------------------
(1) A310-200 series airplanes..... Within 950 flight cycles Within 50 flight cycles or 950 flight cycles or
or 1,900 flight hours 250 flight hours after 1,900 flight hours,
since the last inspection the effective date of whichever occurs
required by paragraph this AD, whichever occurs first.
(f)(1)(ii) or (i) of this first.
AD, whichever occurs
first.
(2) A310-300 series airplanes Within 900 flight cycles Within 50 flight cycles or 900 flight cycles or
(short range). or 2,550 flight hours 250 flight hours after 2,550 flight hours,
since the last inspection the effective date of whichever occurs
required by paragraph this AD, whichever occurs first.
(f)(1)(ii) or (i) of this first.
AD, whichever occurs
first.
(3) A310-300 series airplanes Within 800 flight cycles Within 50 flight cycles or 800 flight cycles or
(long range). or 4,000 flight hours 250 flight hours after 4,000 flight hours,
since the last inspection the effective date of whichever occurs
required by paragraph this AD, whichever occurs first.
(f)(1)(ii) or (i) of this first.
AD, whichever occurs
first.
----------------------------------------------------------------------------------------------------------------
Revised Threshold for Replacing the Pick-Up Angles
(o) As of the effective date of this AD, do the replacement of
the pick-up angle required by paragraph (f)(2) of this AD, at the
applicable time specified in Table 2 of this AD.
Table 2--Revised Thresholds for Replacing Pick-Up Angles
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
For model-- Replace at the earlier of the following times--
----------------------------------------------------------------------------------------------------------------
(1) A310-200 series airplanes......... At the time specified in Within 1,500 flight cycles or 3,000
paragraph (f)(2) of this AD flight hours since the last detailed
for replacing the pick-up inspection, or within 30 days after the
angle. effective date of this AD, whichever
occurs later.
(2) A310-300 series airplanes (short At the time specified in Within 1,600 flight cycles or 4,600
range). paragraph (f)(2) of this AD flight hours since the last detailed
for replacing the pick-up inspection, or within 30 days after the
angle. effective date of this AD, whichever
occurs later.
(3) A310-300 series airplanes (long At the time specified in Within 1,400 flight cycles or 7,200
range). paragraph (f)(2) of this AD flight hours since the last detailed
for replacing the pick-up inspection, or within 30 days after the
angle. effective date of this AD, whichever
occurs later.
----------------------------------------------------------------------------------------------------------------
Optional Terminating Modification
(p) Remove the existing pick-up angles and install a reinforced
doubler between frames (FR) FR40 and FR41, and perform applicable
related investigative and corrective actions by accomplishing all
the applicable actions specified in the Accomplishment Instructions
of Airbus Service Bulletin A310-53-2119, Revision 01, dated February
27, 2007; except as provided by paragraph (q) of this AD.
Accomplishing these actions ends the repetitive inspections required
by this AD.
(q) If any crack is detected and Airbus Service Bulletin A310-
53-2119, Revision 01, dated February 27, 2007, specifies to contact
Airbus: Before further flight, repair the crack 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).
(r) Actions done before the effective date of this AD in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-53-2119, dated October 25, 2005, are acceptable for
compliance with the corresponding requirements of paragraph (p) of
this AD.
Alternative Methods of Compliance (AMOCs)
(s) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Dan
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
Related Information
(t) EASA airworthiness directive 2007-0184, dated July 3, 2007,
also addresses the subject of this AD.
Issued in Renton, Washington, on August 18, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-19715 Filed 8-25-08; 8:45 am]
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