Airworthiness Directives; Airbus Model A300-600 Series Airplanes and Model A310 Series Airplanes, 45305-45308 [E7-15589]
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45305
Rules and Regulations
Federal Register
Vol. 72, No. 156
Tuesday, August 14, 2007
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28159; Directorate
Identifier 2006–NM–257–AD; Amendment
39–15156; AD 2007–16–17]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300–600 Series Airplanes and Model
A310 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
sroberts on PROD1PC70 with RULES
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Airbus Model
A300–600, A310–200, and A310–300
series airplanes. That AD currently
requires inspecting for certain serial
numbers on elevators, and doing a
detailed inspection, visual inspection
with a low-angle light, and tap-test
inspection of the upper and lower
surfaces of the external skins on certain
identified elevators for any damage (i.e.,
debonding of the graphite fiber
reinforced plastic/Tedlar film
protection, bulges, debonding of the
honeycomb core to the carbon fiber
reinforced plastic, abnormal surface
reflections, and torn-out plies), and
doing corrective actions if necessary.
This new AD also requires inspecting
for damage of the identified elevators in
accordance with a new repetitive
inspection program, at new repetitive
intervals; and would provide an
optional terminating action for the
repetitive inspections. This AD results
from reports of damage caused by
moisture/water inside the elevator. We
are issuing this AD to detect and correct
debonding of the skins on the elevators,
which could cause reduced structural
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15:59 Aug 13, 2007
Jkt 211001
integrity of an elevator and reduced
controllability of the airplane.
DATES: This AD becomes effective
September 18, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of September 18, 2007.
On February 3, 2006 (70 FR 77301,
December 30, 2005), the Director of the
Federal Register approved the
incorporation by reference of Airbus All
Operators Telex A300–600–55A6032,
dated June 23, 2004; and Airbus All
Operators Telex A310–55A2033, dated
June 23, 2004.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
ground floor of the West Building at the
DOT street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2005–26–17, amendment
39–14438 (70 FR 77301, December 30,
2005). The existing AD applies to
certain Airbus Model A300–600, A310–
200, and A310–300 series airplanes.
That NPRM was published in the
Federal Register on May 16, 2007 (72
FR 27493). That NPRM proposed to
continue to require inspecting for
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certain serial numbers on elevators, and
doing a detailed inspection, visual
inspection with a low-angle light, and
tap-test inspection of the upper and
lower surfaces of the external skins on
certain identified elevators for any
damage (i.e., debonding of the graphite
fiber reinforced plastic (GFRP)/Tedlar
film protection, bulges, debonding of
the honeycomb core to the carbon fiber
reinforced plastic, abnormal surface
reflections, and torn-out plies), and
doing corrective actions if necessary.
That NPRM also proposed to require
inspecting for damage of the identified
elevators in accordance with a new
repetitive inspection program, at new
repetitive intervals; and would provide
an optional terminating action for the
repetitive inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been received on the NPRM or on
the determination of the cost to the
public.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the change
described previously. We have
determined that this change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Interim Action
We consider this AD interim action.
We are currently considering requiring
the optional terminating action of
replacing the external GFRP/Tedlar film
with an application of pore filler on the
whole elevator external surface, which
would constitute terminating action for
the repetitive inspections required by
this AD.
Costs of Compliance
This AD affects about 142 airplanes of
U.S. registry. The following table
provides the estimated costs for U.S.
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Federal Register / Vol. 72, No. 156 / Tuesday, August 14, 2007 / Rules and Regulations
operators to comply with this AD. The
average labor rate is $80 per work hour.
Action
Work hours
Inspection for serial number (required by AD 2005–
26–17).
Repetitive inspections (required by AD 2005–26–17)
1 ..............................
$0
$80 ..................................
$11,360.
3 ..............................
0
New repetitive inspection program (new action) ........
Between 8 and 12 ..
0
$240, per inspection
cycle.
Between $640 and $960,
per inspection cycle.
Replacement (optional terminating/new action) .........
48 ............................
90
$3,930 .............................
$34,080, per inspection
cycle.
Between $90,880 and
$136,320, per inspection cycle.
$558,060.
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
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We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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15:59 Aug 13, 2007
Jkt 211001
Parts
Cost per airplane
Fleet cost
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
reinforced plastic (GFRP)/Tedlar film as
external protection, with part numbers (P/Ns)
and serial numbers (S/Ns) identified in
Airbus Service Bulletin A300–55–6039 or
A310–55–2040, both dated June 7, 2006.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Unsafe Condition
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14438 (70
FR 77301, December 30, 2005) and by
adding the following new airworthiness
directive (AD):
I
2007–16–17 Airbus: Amendment 39–15156.
Docket No. FAA–2007–28159;
Directorate Identifier 2006–NM–257–AD.
Effective Date
(a) This AD becomes effective September
18, 2007.
Affected ADs
(b) This AD supersedes AD 2005–26–17.
Applicability
(c) This AD applies to Airbus Model A300–
600 series airplanes and Model A310 series
airplanes, certificated in any category,
equipped with carbon fiber reinforced plastic
(CFRP) elevator skin panels, modified in
accordance with Airbus Service Bulletin
A310–55–2019 or A300–55–6016 (Airbus
Modification 10861) with graphite fiber
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(d) This AD results from reports of damage
caused by moisture/water inside the elevator.
We are issuing this AD to detect and correct
debonding of the skins on the elevators,
which could cause reduced structural
integrity of an elevator and reduced
controllability of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of the Requirements of AD
2005–26–17
Inspection for Serial Number, Repetitive
Inspections, and Corrective Actions
(f) Within 600 flight hours after February
3, 2006 (the effective date of AD 2005–26–
17), inspect to determine if the S/N of the
elevator is listed in Airbus All Operators
Telex (AOT) A300–600–55A6032, dated June
23, 2004, or Airbus Service Bulletin A300–
55–6039, dated June 7, 2006 (for Model
A300–600 series airplanes); or in Airbus AOT
A310–55A2033, dated June 23, 2004, or
Airbus Service Bulletin A310–55–2040,
dated June 7, 2006 (for Model A310 series
airplanes).
(1) If the S/N does not match any S/N on
either AOT or service bulletin S/N list, no
further action is required by this paragraph.
(2) If the S/N matches a S/N listed in an
AOT or service bulletin, before further flight,
do the actions listed in Table 1 of this AD,
and any corrective action as applicable, in
accordance with Airbus AOT A300–600–
55A6032, dated June 23, 2004; or Airbus
AOT A310–55A2033, dated June 23, 2004; as
applicable. Repeat the inspections thereafter
at intervals not to exceed 600 flight hours
until the inspection required by paragraph (j)
of this AD is accomplished. Do applicable
corrective actions before further flight.
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Federal Register / Vol. 72, No. 156 / Tuesday, August 14, 2007 / Rules and Regulations
45307
TABLE 1.—REPETITIVE INSPECTIONS
Do a—
Of the—
For any—
Detailed inspection .............................................
Elevator upper and lower external skin surfaces.
Visual inspection with a low-angle light .............
Elevator upper and lower external skin surfaces.
Upper and lower external skin surfaces of the
honeycomb core panels in the elevator.
Damage (i.e., breaks in the graphite fiber reinforced plastic (GFRP)/Tedlar film protection,
debonded GFRP/Tedlar film protection,
bulges, torn-out plies).
Differences in the surface reflection.
Tap-test inspection .............................................
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 mirrors magnifying
lenses, etc. may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Repair Approval
(g) Where the AOTs specified in paragraph
(f) of this AD say to contact the manufacturer
for repair instructions, or an alternative
inspection method: Before further flight,
repair or do the alternative inspection
method according to a method approved by
either the Manager, International Branch,
ANM–116, FAA, Transport Airplane
Directorate; or the Direction Gonorale de
l’Aviation Civile (DGAC) (or its delegated
agent), or the European Aviation Safety
Agency (EASA) (or its delegated agent).
Parts Installation
(h) As of February 3, 2006, no carbon fiber
elevator having part number (P/N)
A55276055000 (left-hand side) or P/N
A55276056000 (right-hand side) may be
installed on any airplane unless it is
inspected according to paragraph (f) of this
AD; or according to paragraph (j) of this AD.
No Reporting Required for AOT Inspections
(i) Although the AOTs referenced in
paragraph (f) of this AD specify to submit
inspection reports to the manufacturer, this
AD does not include that requirement.
New Requirements of This AD
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Revised Inspection Program
(j) For airplanes with affected serial
numbers identified in paragraph (f) of this
AD: Except as provided by paragraph (k) of
this AD, within 2,000 flight cycles or 18
months after the effective date of this AD,
whichever occurs earlier, do a detailed
inspection of the external surfaces of the
GFRP/Tedlar film protection on the upper
and lower skin panels to detect damage of the
film, and a thermographic inspection of the
upper and lower skin panels to detect any
potential water indication inside the panel’s
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15:59 Aug 13, 2007
Jkt 211001
honeycomb core; do all applicable related
investigative/corrective actions before further
flight; and repair the external GFRP/Tedlar
film with pore filler. Do all actions in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
55–6039 (for Model A300–600 series
airplanes), or Airbus Service Bulletin A310–
55–2040 (for Model A310 series airplanes);
both including Appendix 01, both dated June
7, 2006. Repeat the inspections thereafter at
intervals not to exceed 2,000 flight cycles or
18 months, whichever occurs earlier. Where
the service bulletin says to contact the
manufacturer for repair instructions: Before
further flight, repair or do the alternative
inspection method according to a method
approved by either the Manager,
International Branch, ANM–116; or the
EASA (or its delegated agent). Doing the
inspections in accordance with this
paragraph terminates the repetitive
inspection requirements of paragraph (f) of
this AD.
(k) The maximum time between the
inspection required by paragraph (f) of this
AD and the first inspection done in
accordance with paragraph (j) of this AD
must be no greater than: For the
thermographic inspection, 2,500 flight hours
after the last thermographic inspection done
in accordance with the applicable AOT
specified in paragraph (f) of this AD; and for
the tap test, 600 flight hours after the last tap
test inspection done in accordance with the
applicable AOT specified in paragraph (f) of
this AD.
Report
(l) Submit a report of the findings (both
positive and negative) of the inspections
required by paragraph (j) of this AD to
Airbus, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France, at the
applicable time specified in paragraph (l)(1)
or (l)(2) of this AD. The report must include
the information in Appendix 01 of Airbus
Service Bulletin A300–55–6039 or Airbus
Service Bulletin A310–55–2040, both dated
June 7, 2006, as applicable. Under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
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Honeycomb core that has debonded from the
carbon fiber reinforced plastic (CFRP).
(1) If the inspection was done after the
effective date of this AD: Submit the report
within 30 days after the inspection.
(2) If the inspection was done prior to the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
Optional Terminating Action
(m) Replacing the external GFRP/Tedlar
film with an application of pore filler on the
whole elevator external surface in accordance
with Airbus Service Bulletin A300–55–6040
(for Model A300–600 series airplanes), or
Airbus Service Bulletin A310–55–2041 (for
Model A310 series airplanes), both dated
June 5, 2006, terminates the repetitive
inspection requirements of paragraph (j) of
this AD, provided the replacement is done
before further flight after accomplishment of
Airbus Service Bulletins A310–55–2040 and
A300–55–6039, both dated June 7, 2006.
Alternative Methods of Compliance
(AMOCs)
(n)(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) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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.
(3) AMOCs approved previously in
accordance with AD 2005–26–17 are
approved as AMOCs with the corresponding
provisions of this AD.
Related Information
(o) EASA airworthiness directive 2006–
0289, dated November 2, 2006, also
addresses the subject of this AD.
Material Incorporated by Reference
(p) You must use the service documents
identified in Table 2 of this AD to perform
the actions that are required by this AD,
unless the AD specifies otherwise.
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Federal Register / Vol. 72, No. 156 / Tuesday, August 14, 2007 / Rules and Regulations
TABLE 2.—REQUIRED MATERIAL INCORPORATED BY REFERENCE
Airbus service information
Date
All Operators Telex A300–600–55A6032 .........................................................................................................................................
All Operators Telex A310–55A2033 .................................................................................................................................................
Service Bulletin A300–55–6039, including Appendix 01 ..................................................................................................................
Service Bulletin A310–55–2040, including Appendix 01 ..................................................................................................................
If you accomplish the optional actions
specified in this AD, you must use the
service documents identified in Table 3 of
June
June
June
June
23, 2004.
23, 2004.
7, 2006.
7, 2006.
this AD to perform those actions, unless the
AD specifies otherwise.
TABLE 3.—OPTIONAL MATERIAL INCORPORATED BY REFERENCE
Airbus service information
Date
Service Bulletin A300–55–6040 .......................................................................................................................................................
Service Bulletin A310–55–2041 .......................................................................................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the documents identified in Table 4 of this
June 5, 2006.
June 5, 2006.
AD in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
TABLE 4.—NEW MATERIAL INCORPORATED BY REFERENCE
Airbus service information
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
Date
A300–55–6039, including Appendix 01 ..................................................................................................................
A300–55–6040 .......................................................................................................................................................
A310–55–2040, including Appendix 01 ..................................................................................................................
A310–55–2041 .......................................................................................................................................................
(2) On February 3, 2006 (70 FR 77301,
December 30, 2005), the Director of the
Federal Register approved the incorporation
June
June
June
June
7,
5,
7,
5,
2006.
2006.
2006.
2006.
by reference of the service documents
identified in Table 5 of this AD.
TABLE 5.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Airbus service information
Date
All Operators Telex A300–600–55A6032 .........................................................................................................................................
All Operators Telex A310–55A2033 .................................................................................................................................................
(3) Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for a
copy of this service information. You may
review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
sroberts on PROD1PC70 with RULES
Issued in Renton, Washington, on August
2, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–15589 Filed 8–13–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21238; Directorate
Identifier 2005–NE–12–AD; Amendment 39–
15159; AD 2007–17–01]
RIN 2120–AA64
Airworthiness Directives; General
Electric (GE) CF6–80E1 Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
General Electric (GE) CF6–80E1 series
VerDate Aug<31>2005
15:59 Aug 13, 2007
Jkt 211001
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June 23, 2004.
June 23, 2004.
turbofan engines. That AD currently
requires removing electronic control
unit (ECU) software version E.1.M. or
earlier installed software, and installing
improved software for the ECU. This AD
requires removing software version
E.1.N or earlier from the engine ECU.
Engines with the new version software
will have increased margin to flameout.
This AD results from reports of engine
flameout events during flight, including
reports of events where all engines
simultaneously experienced a flameout
or other adverse operation. Although the
root cause investigation is not yet
complete, we believe that exposure to
ice crystals during flight is associated
with these flameout events. We are
issuing this AD to minimize the
potential of an all-engine flameout event
caused by ice accretion and shedding
during flight.
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]]>Agencies
[Federal Register Volume 72, Number 156 (Tuesday, August 14, 2007)]
[Rules and Regulations]
[Pages 45305-45308]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-15589]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 72, No. 156 / Tuesday, August 14, 2007 /
Rules and Regulations
[[Page 45305]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28159; Directorate Identifier 2006-NM-257-AD;
Amendment 39-15156; AD 2007-16-17]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300-600 Series Airplanes
and Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Airbus Model A300-600, A310-200, and
A310-300 series airplanes. That AD currently requires inspecting for
certain serial numbers on elevators, and doing a detailed inspection,
visual inspection with a low-angle light, and tap-test inspection of
the upper and lower surfaces of the external skins on certain
identified elevators for any damage (i.e., debonding of the graphite
fiber reinforced plastic/Tedlar film protection, bulges, debonding of
the honeycomb core to the carbon fiber reinforced plastic, abnormal
surface reflections, and torn-out plies), and doing corrective actions
if necessary. This new AD also requires inspecting for damage of the
identified elevators in accordance with a new repetitive inspection
program, at new repetitive intervals; and would provide an optional
terminating action for the repetitive inspections. This AD results from
reports of damage caused by moisture/water inside the elevator. We are
issuing this AD to detect and correct debonding of the skins on the
elevators, which could cause reduced structural integrity of an
elevator and reduced controllability of the airplane.
DATES: This AD becomes effective September 18, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of September 18,
2007.
On February 3, 2006 (70 FR 77301, December 30, 2005), the Director
of the Federal Register approved the incorporation by reference of
Airbus All Operators Telex A300-600-55A6032, dated June 23, 2004; and
Airbus All Operators Telex A310-55A2033, dated June 23, 2004.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue, SE., Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the AD docket on the Internet at https://dms.dot.gov
or in person at the Docket Operations office between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The Docket Operations
office (telephone (800) 647-5527) is located on the ground floor of the
West Building at the DOT street address stated in the ADDRESSES
section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2005-26-17, amendment
39-14438 (70 FR 77301, December 30, 2005). The existing AD applies to
certain Airbus Model A300-600, A310-200, and A310-300 series airplanes.
That NPRM was published in the Federal Register on May 16, 2007 (72 FR
27493). That NPRM proposed to continue to require inspecting for
certain serial numbers on elevators, and doing a detailed inspection,
visual inspection with a low-angle light, and tap-test inspection of
the upper and lower surfaces of the external skins on certain
identified elevators for any damage (i.e., debonding of the graphite
fiber reinforced plastic (GFRP)/Tedlar film protection, bulges,
debonding of the honeycomb core to the carbon fiber reinforced plastic,
abnormal surface reflections, and torn-out plies), and doing corrective
actions if necessary. That NPRM also proposed to require inspecting for
damage of the identified elevators in accordance with a new repetitive
inspection program, at new repetitive intervals; and would provide an
optional terminating action for the repetitive inspections.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been received on the NPRM or
on the determination of the cost to the public.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD with the
change described previously. We have determined that this change will
neither increase the economic burden on any operator nor increase the
scope of the AD.
Interim Action
We consider this AD interim action. We are currently considering
requiring the optional terminating action of replacing the external
GFRP/Tedlar film with an application of pore filler on the whole
elevator external surface, which would constitute terminating action
for the repetitive inspections required by this AD.
Costs of Compliance
This AD affects about 142 airplanes of U.S. registry. The following
table provides the estimated costs for U.S.
[[Page 45306]]
operators to comply with this AD. The average labor rate is $80 per
work hour.
----------------------------------------------------------------------------------------------------------------
Action Work hours Parts Cost per airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
Inspection for serial number 1.................... $0 $80................. $11,360.
(required by AD 2005-26-17).
Repetitive inspections (required 3.................... 0 $240, per inspection $34,080, per
by AD 2005-26-17). cycle. inspection cycle.
New repetitive inspection program Between 8 and 12..... 0 Between $640 and Between $90,880 and
(new action). $960, per $136,320, per
inspection cycle. inspection cycle.
Replacement (optional terminating/ 48................... 90 $3,930.............. $558,060.
new action).
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14438 (70 FR 77301, December 30, 2005) and by
adding the following new airworthiness directive (AD):
2007-16-17 Airbus: Amendment 39-15156. Docket No. FAA-2007-28159;
Directorate Identifier 2006-NM-257-AD.
Effective Date
(a) This AD becomes effective September 18, 2007.
Affected ADs
(b) This AD supersedes AD 2005-26-17.
Applicability
(c) This AD applies to Airbus Model A300-600 series airplanes
and Model A310 series airplanes, certificated in any category,
equipped with carbon fiber reinforced plastic (CFRP) elevator skin
panels, modified in accordance with Airbus Service Bulletin A310-55-
2019 or A300-55-6016 (Airbus Modification 10861) with graphite fiber
reinforced plastic (GFRP)/Tedlar film as external protection, with
part numbers (P/Ns) and serial numbers (S/Ns) identified in Airbus
Service Bulletin A300-55-6039 or A310-55-2040, both dated June 7,
2006.
Unsafe Condition
(d) This AD results from reports of damage caused by moisture/
water inside the elevator. We are issuing this AD to detect and
correct debonding of the skins on the elevators, which could cause
reduced structural integrity of an elevator and reduced
controllability of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of the Requirements of AD 2005-26-17
Inspection for Serial Number, Repetitive Inspections, and Corrective
Actions
(f) Within 600 flight hours after February 3, 2006 (the
effective date of AD 2005-26-17), inspect to determine if the S/N of
the elevator is listed in Airbus All Operators Telex (AOT) A300-600-
55A6032, dated June 23, 2004, or Airbus Service Bulletin A300-55-
6039, dated June 7, 2006 (for Model A300-600 series airplanes); or
in Airbus AOT A310-55A2033, dated June 23, 2004, or Airbus Service
Bulletin A310-55-2040, dated June 7, 2006 (for Model A310 series
airplanes).
(1) If the S/N does not match any S/N on either AOT or service
bulletin S/N list, no further action is required by this paragraph.
(2) If the S/N matches a S/N listed in an AOT or service
bulletin, before further flight, do the actions listed in Table 1 of
this AD, and any corrective action as applicable, in accordance with
Airbus AOT A300-600-55A6032, dated June 23, 2004; or Airbus AOT
A310-55A2033, dated June 23, 2004; as applicable. Repeat the
inspections thereafter at intervals not to exceed 600 flight hours
until the inspection required by paragraph (j) of this AD is
accomplished. Do applicable corrective actions before further
flight.
[[Page 45307]]
Table 1.--Repetitive Inspections
------------------------------------------------------------------------
Do a-- Of the-- For any--
------------------------------------------------------------------------
Detailed inspection......... Elevator upper and Damage (i.e., breaks
lower external skin in the graphite
surfaces. fiber reinforced
plastic (GFRP)/
Tedlar film
protection,
debonded GFRP/
Tedlar film
protection, bulges,
torn-out plies).
Visual inspection with a low- Elevator upper and Differences in the
angle light. lower external skin surface reflection.
surfaces.
Tap-test inspection......... Upper and lower Honeycomb core that
external skin has debonded from
surfaces of the the carbon fiber
honeycomb core reinforced plastic
panels in the (CFRP).
elevator.
------------------------------------------------------------------------
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
mirrors magnifying lenses, etc. may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repair Approval
(g) Where the AOTs specified in paragraph (f) of this AD say to
contact the manufacturer for repair instructions, or an alternative
inspection method: Before further flight, repair or do the
alternative inspection method according to a method approved by
either the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate; or the Direction Gonorale de l'Aviation Civile
(DGAC) (or its delegated agent), or the European Aviation Safety
Agency (EASA) (or its delegated agent).
Parts Installation
(h) As of February 3, 2006, no carbon fiber elevator having part
number (P/N) A55276055000 (left-hand side) or P/N A55276056000
(right-hand side) may be installed on any airplane unless it is
inspected according to paragraph (f) of this AD; or according to
paragraph (j) of this AD.
No Reporting Required for AOT Inspections
(i) Although the AOTs referenced in paragraph (f) of this AD
specify to submit inspection reports to the manufacturer, this AD
does not include that requirement.
New Requirements of This AD
Revised Inspection Program
(j) For airplanes with affected serial numbers identified in
paragraph (f) of this AD: Except as provided by paragraph (k) of
this AD, within 2,000 flight cycles or 18 months after the effective
date of this AD, whichever occurs earlier, do a detailed inspection
of the external surfaces of the GFRP/Tedlar film protection on the
upper and lower skin panels to detect damage of the film, and a
thermographic inspection of the upper and lower skin panels to
detect any potential water indication inside the panel's honeycomb
core; do all applicable related investigative/corrective actions
before further flight; and repair the external GFRP/Tedlar film with
pore filler. Do all actions in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-55-6039 (for Model
A300-600 series airplanes), or Airbus Service Bulletin A310-55-2040
(for Model A310 series airplanes); both including Appendix 01, both
dated June 7, 2006. Repeat the inspections thereafter at intervals
not to exceed 2,000 flight cycles or 18 months, whichever occurs
earlier. Where the service bulletin says to contact the manufacturer
for repair instructions: Before further flight, repair or do the
alternative inspection method according to a method approved by
either the Manager, International Branch, ANM-116; or the EASA (or
its delegated agent). Doing the inspections in accordance with this
paragraph terminates the repetitive inspection requirements of
paragraph (f) of this AD.
(k) The maximum time between the inspection required by
paragraph (f) of this AD and the first inspection done in accordance
with paragraph (j) of this AD must be no greater than: For the
thermographic inspection, 2,500 flight hours after the last
thermographic inspection done in accordance with the applicable AOT
specified in paragraph (f) of this AD; and for the tap test, 600
flight hours after the last tap test inspection done in accordance
with the applicable AOT specified in paragraph (f) of this AD.
Report
(l) Submit a report of the findings (both positive and negative)
of the inspections required by paragraph (j) of this AD to Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, at the
applicable time specified in paragraph (l)(1) or (l)(2) of this AD.
The report must include the information in Appendix 01 of Airbus
Service Bulletin A300-55-6039 or Airbus Service Bulletin A310-55-
2040, both dated June 7, 2006, as applicable. Under the provisions
of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office
of Management and Budget (OMB) has approved the information
collection requirements contained in this AD and has assigned OMB
Control Number 2120-0056.
(1) If the inspection was done after the effective date of this
AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done prior to the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
Optional Terminating Action
(m) Replacing the external GFRP/Tedlar film with an application
of pore filler on the whole elevator external surface in accordance
with Airbus Service Bulletin A300-55-6040 (for Model A300-600 series
airplanes), or Airbus Service Bulletin A310-55-2041 (for Model A310
series airplanes), both dated June 5, 2006, terminates the
repetitive inspection requirements of paragraph (j) of this AD,
provided the replacement is done before further flight after
accomplishment of Airbus Service Bulletins A310-55-2040 and A300-55-
6039, both dated June 7, 2006.
Alternative Methods of Compliance (AMOCs)
(n)(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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
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.
(3) AMOCs approved previously in accordance with AD 2005-26-17
are approved as AMOCs with the corresponding provisions of this AD.
Related Information
(o) EASA airworthiness directive 2006-0289, dated November 2,
2006, also addresses the subject of this AD.
Material Incorporated by Reference
(p) You must use the service documents identified in Table 2 of
this AD to perform the actions that are required by this AD, unless
the AD specifies otherwise.
[[Page 45308]]
Table 2.--Required Material Incorporated by Reference
------------------------------------------------------------------------
Airbus service information Date
------------------------------------------------------------------------
All Operators Telex A300-600-55A6032... June 23, 2004.
All Operators Telex A310-55A2033....... June 23, 2004.
Service Bulletin A300-55-6039, June 7, 2006.
including Appendix 01.
Service Bulletin A310-55-2040, June 7, 2006.
including Appendix 01.
------------------------------------------------------------------------
If you accomplish the optional actions specified in this AD, you
must use the service documents identified in Table 3 of this AD to
perform those actions, unless the AD specifies otherwise.
Table 3.--Optional Material Incorporated by Reference
------------------------------------------------------------------------
Airbus service information Date
------------------------------------------------------------------------
Service Bulletin A300-55-6040.......... June 5, 2006.
Service Bulletin A310-55-2041.......... June 5, 2006.
------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the documents identified in Table 4 of
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Table 4.--New Material Incorporated by Reference
------------------------------------------------------------------------
Airbus service information Date
------------------------------------------------------------------------
Service Bulletin A300-55-6039, June 7, 2006.
including Appendix 01.
Service Bulletin A300-55-6040.......... June 5, 2006.
Service Bulletin A310-55-2040, June 7, 2006.
including Appendix 01.
Service Bulletin A310-55-2041.......... June 5, 2006.
------------------------------------------------------------------------
(2) On February 3, 2006 (70 FR 77301, December 30, 2005), the
Director of the Federal Register approved the incorporation by
reference of the service documents identified in Table 5 of this AD.
Table 5.--Material Previously Incorporated by Reference
------------------------------------------------------------------------
Airbus service information Date
------------------------------------------------------------------------
All Operators Telex A300-600-55A6032... June 23, 2004.
All Operators Telex A310-55A2033....... June 23, 2004.
------------------------------------------------------------------------
(3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service information. You may
review copies at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on August 2, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-15589 Filed 8-13-07; 8:45 am]
BILLING CODE 4910-13-P
