Airworthiness Directives; Airbus Model A300 B4-601, A300 B4-603, A300 B4-605R, A300 C4-605R Variant F, A310-204, A310-304, and A310-308 Airplanes Equipped With General Electric CF6-80C2 Engines, 3764-3768 [E7-1207]
Download as PDF
<![CDATA[
3764
Federal Register / Vol. 72, No. 17 / Friday, January 26, 2007 / Proposed Rules
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 supplemental NPRM 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
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Empresa Brasileira De Aeronautica S.A.
(EMBRAER): Docket No. FAA–2006–
25419; Directorate Identifier 2006–NM–
055–AD.
mstockstill on PROD1PC62 with PROPOSALS
Comments Due Date
(a) The FAA must receive comments on
this AD action by February 20, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to EMBRAER Model
ERJ 170–100 LR, –100 STD, –100 SE, –100
SU, –200 LR, –200 STD, and –200 SU
airplanes, certificated in any category; as
identified in EMBRAER Service Bulletin
VerDate Aug<31>2005
15:24 Jan 25, 2007
Jkt 211001
Unsafe Condition
(d) This AD results from reports of certain
lavatory waste compartment doors opening
during flight due to movement of the waste
compartment during takeoff, because the
mini-latches installed on those doors lose
their strength over time. We are issuing this
AD to prevent the inability of the waste
compartment doors to adequately contain a
fire inside the lavatory waste compartment,
and consequent uncontained fire and smoke
within a lavatory during flight.
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.
Replacement of Mini-Latches on Certain
Lavatory Waste Compartment Doors
(f) Within 700 flight hours after the
effective date of this AD: Replace the minilatches for the forward and aft lavatory waste
compartment doors by accomplishing all the
actions, except for the forward and aft
lavatory mirror rework, specified in
paragraphs 3.B. and 3.G. of paragraph 4.,
‘‘Appendix 1,’’ of EMBRAER Service Bulletin
170–25–0024, Revision 01, dated January 9,
2006.
Note 1: EMBRAER Service Bulletin 170–
25–0024, Revision 01, dated January 9, 2006,
refers to C & D Aerospace Service Bulletin
170–18616–25–023, Revision 1, dated
November 29, 2005, as an additional source
of service information for replacing the minilatches on certain lavatory waste
compartment doors required by paragraph (f)
of this AD.
Credit for Actions Done Using Previous Issue
of Service Information
1. The authority citation for part 39
continues to read as follows:
§ 39.13
170–25–0024, Revision 01, dated January 9,
2006.
(g) Replacements done before the effective
date of this AD in accordance with
paragraphs 3.B. and 3.G. of paragraph 4.,
‘‘Appendix 1,’’ of EMBRAER Service Bulletin
170–25–0024, dated July 21, 2005, are
considered acceptable for compliance with
the corresponding action specified in this
AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(i) Brazilian airworthiness directive 2005–
11–01, effective December 8, 2005, also
addresses the subject of this AD.
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
Issued in Renton, Washington, on January
12, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–1215 Filed 1–25–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27012; Directorate
Identifier 2006–NM–188–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B4–601, A300 B4–603, A300 B4–
605R, A300 C4–605R Variant F, A310–
204, A310–304, and A310–308
Airplanes Equipped With General
Electric CF6–80C2 Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Airbus Model A300 B4–600, B4–600R,
C4–605R Variant F, and F4–600R
(collectively called A300–600) series
airplanes; and Model A310 series
airplanes. The existing AD currently
requires a one-time inspection for
damage of the integrated drive generator
(IDG) electrical harness and pyramid
arm, and repair if necessary. This
proposed AD would add new repetitive
inspections, which, when initiated,
would terminate the inspection required
by the existing AD. This proposed AD
would also require repairing damage
and protecting the harness. The
proposed AD would also provide for
optional terminating action for the
repetitive inspections. This proposed
AD also removes certain airplanes from
the applicability of the existing AD.
This proposed AD results from a report
of structural damage on the forward
pyramid arm of an engine pylon due to
chafing of the IDG electrical harness
against the structure of the pyramid
arm. We are proposing this AD to
prevent electrical arcing in the engine
pylon, which could result in loss of the
relevant alternating current (AC) bus
bar, reduced structural integrity of the
engine pylon, and possible loss of
control of the airplane.
DATES: We must receive comments on
this proposed AD by February 26, 2007.
E:\FR\FM\26JAP1.SGM
26JAP1
Federal Register / Vol. 72, No. 17 / Friday, January 26, 2007 / Proposed Rules
Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: 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:
ADDRESSES:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘Docket No. FAA–2007–27012;
Directorate Identifier 2006–NM–188–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
On April 16, 2004, we issued AD
2004–09–01, amendment 39–13590 (69
FR 23090, April 28, 2004), for certain
Airbus Model A300 B4–600, B4–600R,
3765
C4–605R Variant F, and F4–600R
(collectively called A300–600) series
airplanes; and Model A310 series
airplanes. That AD requires a one-time
inspection for damage of the integrated
drive generator (IDG) electrical harness
and pyramid arm, and repair if
necessary. That AD resulted from a
report of structural damage on the
forward pyramid arm of an engine pylon
during a scheduled maintenance check.
Investigation revealed that the damage
was caused by chafing of the IDG
electrical harness against the structure
of the pyramid arm. We issued that AD
to prevent electrical arcing within the
engine pylon, which could result in loss
of the relevant alternating current (AC)
bus bar, reduced structural integrity of
the engine pylon, and possible loss of
control of the airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2004–09–01
explains that we considered the
requirements ‘‘interim action’’ and were
considering further rulemaking. We
have now determined that further
rulemaking is necessary, and this
proposed AD follows from that
determination. Since we issued AD
2004–09–01, the European Aviation
Safety Agency (EASA), which is the
airworthiness authority for the
European Union, has advised us that a
repetitive inspection program is
necessary to ensure the functionality of
the AC bus bar and the structural
integrity of the pylon.
Relevant Service Information
Airbus has issued the service
bulletins identified in the following
table.
SERVICE BULLETINS
Actions
Airbus Service Bulletin
Inspection (repetitive inspections of the IDG
electrical harness and pylon forward pyramid
arms), and protection of the harness.
A300–24–6097, dated March 3, 2006, including Appendix 01.
A300–600 series airplanes.
A310–24–2100, dated March 3, 2006, including Appendix 01.
A300–54–6038, dated May 12, 2006 ..............
A310 series airplanes.
A310–54–2039, dated May 12, 2006 ..............
A310 series airplanes.
mstockstill on PROD1PC62 with PROPOSALS
Modification (replacement of the bracket feeder
on the pylons).
Service Bulletins A300–24–6097 and
A310–24–2100 describe procedures for:
• Doing a detailed visual inspection
for wear on the pyramid arms;
• Repairing wear that is within
certain limits;
• Contacting Airbus for repair
instructions if the wear exceeds those
limits;
VerDate Aug<31>2005
15:24 Jan 25, 2007
Jkt 211001
• Doing a detailed visual inspection
of the cables;
• Repairing damaged cables;
• Protecting the harness, including
installing adhesive tape, lacing tape,
and adhesive sealant; and
• Reporting inspection results to
Airbus.
The modification described in Service
Bulletins A300–54–6038 and A310–54–
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
Affected model
A300–600 series airplanes.
2039 eliminates the need for the
repetitive inspections specified above.
Accomplishing the actions specified
in Service Bulletins A300–24–6097 and
A310–24–2100 is intended to
adequately address the unsafe
condition. The EASA mandated that
service information and issued
airworthiness directive 2006–0155,
E:\FR\FM\26JAP1.SGM
26JAP1
3766
Federal Register / Vol. 72, No. 17 / Friday, January 26, 2007 / Proposed Rules
dated June 1, 2006, to ensure the
continued airworthiness of these
airplanes in the European Union. EASA
airworthiness directive 2006–0155
superseded French airworthiness
directive F–2004–039 (referenced in
FAA AD 2004–09–01). The EASA
provided for the bracket feeder
replacement as optional terminating
action to the repetitive inspections.
FAA’s Determination and Requirements
of the Proposed AD
These airplane models 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 we
need to issue an AD for airplanes of this
type design that are certificated for
operation in the United States.
This proposed AD would:
• Supersede AD 2004–09–01;
• Retain the requirements of AD
2004–09–01;
• Require new repetitive inspections
for damage of the IDG electrical harness
and pylon forward pyramid arms,
which, when initiated, would terminate
the inspection required by AD 2004–09–
01;
• Require repairing damage and
protecting the harness;
• Provide for optional terminating
action for the repetitive inspections;
• Remove certain airplanes (including
certain Model A300–600 and Model
A310 series airplanes and those
modified in production) from the
applicability of AD 2004–09–01; and
• Require sending the inspection
results to Airbus for each repetitive
inspection.
Differences Between Proposed AD and
Service Information/EASA
Airworthiness Directive
The applicability of EASA
airworthiness directive 2006–0155
excludes airplanes on which the actions
specified in Airbus Service Bulletin
A300–54–6038 or A310–54–2039 have
been done in service. However, we have
not excluded those airplanes in the
applicability of this proposed AD;
rather, this proposed AD would provide
for that modification as an option to the
required repetitive inspections.
Including these actions would ensure
that the repetitive inspections would
continue on all affected airplanes until
accomplishment of the modification
would allow the inspections to be
terminated. Operators must continue to
operate the airplane in the configuration
required by this proposed AD unless an
alternative method of compliance is
approved.
Service Bulletins A300–24–6097 and
A310–24–2100 specify to contact the
manufacturer for instructions on how to
repair certain conditions, but paragraph
(k) of this proposed AD would require
repairing those conditions using a
method approved by the FAA or the
EASA (or its delegated agent). In light of
the type of repair that would be required
to address the unsafe condition, and
consistent with existing bilateral
airworthiness agreements, we have
determined that, for this proposed AD,
a repair approved by either the FAA or
the EASA would be acceptable for
compliance with paragraph (k) of this
proposed AD.
Clarification of Inspection Terminology
The ‘‘detailed visual inspection’’
specified in Service Bulletins A300–24–
6097 and A310–24–2100 is referred to
as a ‘‘detailed inspection’’ in this
proposed AD. Note 1 in this proposed
AD identifies a detailed inspection.
Explanation of Changes Made to
Requirements of Existing AD
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved alternative method of
compliance (AMOC) on any airplane to
which the AMOC applies.
Paragraph (e) of the existing AD
specifies repairing certain discrepancies
using a method approved by either the
´ ´
FAA or the Direction Generale de
l’Aviation Civile (DGAC) (or its
delegated agent). The EASA has
assumed responsibility for the airplane
models that would be subject to this AD.
Therefore, we have revised
corresponding paragraph (i) in this
proposed AD to specify the repair of
those discrepancies before the effective
date of the new AD using a method
approved by the FAA, the DGAC (or its
delegated agent), or the EASA (or its
delegated agent). After the effective
date, paragraph (i) of this proposed AD
specifies the repair using a method
approved by the FAA or the EASA (or
its delegated agent).
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Work hours
mstockstill on PROD1PC62 with PROPOSALS
One-time inspection
(from AD 2004–09–
01).
Repetitive inspections
and harness protection (new proposed
requirement).
New optional modification.
Average
labor rate
per hour
2
$80
$0
4
80
0
8
80
2,460
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
VerDate Aug<31>2005
15:24 Jan 25, 2007
Cost per airplane
Jkt 211001
Number of U.S.-registered
airplanes
$160 ............................
100 ..............................
$16,000.
$320, per inspection
cycle.
100 ..............................
$32,000, per inspection cycle.
$3,100 .........................
Up to 100 ....................
Up to $310,000.
Cost of
parts
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
Fleet cost
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
E:\FR\FM\26JAP1.SGM
26JAP1
Federal Register / Vol. 72, No. 17 / Friday, January 26, 2007 / Proposed Rules
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.
mstockstill on PROD1PC62 with PROPOSALS
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13590 (69
FR 23090, April 28, 2004) and adding
the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2007–27012;
Directorate Identifier 2006–NM–188–AD.
VerDate Aug<31>2005
15:24 Jan 25, 2007
Jkt 211001
Comments Due Date
(a) The FAA must receive comments on
this AD action by February 26, 2007.
Affected ADs
(b) This AD supersedes AD 2004–09–01.
Applicability
(c) This AD applies to Airbus Model A300
B4–601, A300 B4–603, A300 B4–605R, A300
C4–605R Variant F, A310–204, A310–304,
and A310–308 airplanes; certificated in any
category; equipped with General Electric
CF6–80C2 engines without full-authority
digital electronic control (FADEC); excluding
airplanes on which Airbus Modification
13184 was done in production.
Unsafe Condition
(d) This AD results from a report of
structural damage on the forward pyramid
arm of an engine pylon due to chafing of the
integrated drive generator (IDG) electrical
harness against the structure of the pyramid
arm. We are issuing this AD to prevent
electrical arcing in the engine pylon, which
could result in loss of the relevant alternating
current (AC) bus bar, reduced structural
integrity of the engine pylon, and possible
loss of control of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD
2004–09–01
All Operators Telex Reference
(f) The term ‘‘All Operators Telex,’’ or
‘‘AOT,’’ as used in paragraphs (g), (h), and (j)
of this AD, means the following AOTs, as
applicable:
(1) For Model A300 B4–601, A300 B4–603,
A300 B4–605R, and A300 C4–605R Variant F
airplanes: Airbus AOT A300–54A6037, dated
February 19, 2004; and
(2) For Model A310–204, A310–304, and
–308 airplanes: Airbus AOT A310–54A2038,
dated February 19, 2004.
Inspection
(g) At the applicable time in paragraph
(g)(1) or (g)(2) of this AD, do a one-time
detailed inspection for discrepancies of the
IDG harness, harness bracket, retaining
fasteners, and pyramid arm, in accordance
with the applicable AOT.
(1) For airplanes on which Airbus
Modification 07591 has not been
incorporated as of May 13, 2004 (the effective
date of AD 2004–09–01): Within 10 days after
May 13, 2004.
(2) For airplanes on which Airbus
Modification 07591 has been incorporated as
of May 13, 2004: Within 600 flight hours after
May 13, 2004.
Note 1: 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
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
3767
the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.’’
Related Investigative and Corrective Actions
for Damaged Electrical Harness
(h) If any discrepancy in the IDG electrical
harness, fretting at the convoluted conduits,
or contact between the IDG electrical harness
and the pyramid arms is found during the
inspection required by paragraph (g) of this
AD: Before further flight, do the applicable
related investigative actions and corrective
actions in accordance with the applicable
AOT.
Corrective Action for Damaged Electrical
Harness Bracket, Retaining Fasteners, or
Pyramid Arm
(i) If any discrepancy in the electrical
harness bracket, retaining fasteners, or
pyramid arm is found during the inspection
required by paragraph (g) of this AD: Before
further flight, repair in accordance with a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; the Direction
´ ´
Generale de l’Aviation Civile (DGAC) (or its
delegated agent); or the European Aviation
Safety Agency (EASA) (or its delegated
agent). After the effective date of this AD,
repair in accordance with a method approved
by the FAA or the EASA.
No Reporting Requirement for Paragraph (g)
of This AD
(j) Although the referenced AOTs describe
procedures for submitting certain
information to the manufacturer, no report is
required for the inspection required by
paragraph (g) of this AD.
New Requirements of This AD
Repetitive Inspections
(k) Within 6 months after the effective date
of this AD, and thereafter at intervals not to
exceed 12 months: Do a detailed inspection
for damage of the IDG harness and the pylon
pyramid arms, and protect the harness. Do
the actions in accordance with Airbus
Service Bulletin A300–24–6097, dated March
3, 2006 (for Model A300 B4–601, A300 B4–
603, A300 B4–605R, and A300 C4–605R
Variant F airplanes); or A310–24–2100, dated
March 3, 2006 (for Model A310–204, A310–
304, and A310–308 airplanes). The initial
inspection terminates the requirements of
paragraph (g) of this AD. If any discrepancy
is found: Before further flight, repair in
accordance with the applicable service
bulletin; except, where the service bulletin
specifies to contact the manufacturer for
repair instructions, this AD requires repair
using a method approved by either the
Manager, International Branch, ANM–116; or
the EASA (or its delegated agent).
Report
(l) At the applicable times specified in
paragraphs (l)(1) and (l)(2) of this AD, submit
a report of the findings (both positive and
negative) of each inspection required by
paragraph (k) of this AD. Send the report to
Airbus Customer Services Directorate,
Department AI/SE–E43, 1 Rond Point
E:\FR\FM\26JAP1.SGM
26JAP1
3768
Federal Register / Vol. 72, No. 17 / Friday, January 26, 2007 / Proposed Rules
Maurice Bellonte, 31707 Blagnac, Cedex,
France. The report must include the
information specified in Appendix 01 of
Airbus Service Bulletin A300–24–6097 or
A310–24–2100, both dated March 3, 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) For each inspection done after the
effective date of this AD: Send the report
within 30 days after the inspection.
(2) If an inspection was done before the
effective date of this AD: Send the report
within 30 days after the effective date of this
AD.
Optional Terminating Action
(m) Replacement of the bracket feeder on
the pylons terminates the requirements of
this AD if the bracket feeder is replaced in
accordance with Airbus Service Bulletin
A300–54–6038, dated May 12, 2006 (for
Model A300 B4–601, A300 B4–603, A300
B4–605R, and A300 C4–605R Variant F
airplanes); or A310–54–2039, dated May 12,
2006 (for Model A310–204, A310–304, and
A310–308 airplanes); as applicable.
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) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(o) EASA airworthiness directive 2006–
0155, dated June 1, 2006, also addresses the
subject of this AD.
Issued in Renton, Washington, on
December 26, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–1207 Filed 1–25–07; 8:45 am]
mstockstill on PROD1PC62 with PROPOSALS
BILLING CODE 4910–13–P
VerDate Aug<31>2005
15:24 Jan 25, 2007
Jkt 211001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27015; Directorate
Identifier 2006–NM–169–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318–111 and A318–112 Airplanes and
Model A319, A320, and A321 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede two existing airworthiness
directives (ADs). One AD applies to all
Airbus Model A319 and A320 airplanes
and currently requires repetitive
ultrasonic inspections to detect fatigue
cracking in the wing/fuselage joint
cruciform fittings, and corrective actions
if necessary. The other AD applies to all
Airbus Model A319, A320, and A321
airplanes and currently requires a
revision to the Airworthiness
Limitations section (ALS) of the
Instructions for Continued
Airworthiness (ICA). This proposed AD
would require new revisions to the ALS
of the ICA to incorporate service life
limits for certain items and inspections
to detect fatigue cracking, accidental
damage, or corrosion in certain
structures; and accomplishment of the
repetitive ultrasonic inspections of the
wing/fuselage joint cruciform fittings in
accordance with the revised ALS of the
ICA. This proposed AD would also add
airplanes to the applicability. This
proposed AD results from issuance of
new and more restrictive service life
limits and structural inspections based
on fatigue testing and in-service
findings. We are proposing this AD to
detect and correct fatigue cracking,
accidental damage, or corrosion in
principal structural elements and to
prevent failure of certain life limited
parts, which could result in reduced
structural integrity of the airplane.
DATES: We must receive comments on
this proposed AD by February 26, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
PO 00000
Frm 00019
Fmt 4702
Sfmt 4702
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2141;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘Docket No. FAA–2007–27015;
Directorate Identifier 2006–NM–169–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
E:\FR\FM\26JAP1.SGM
26JAP1
]]>Agencies
[Federal Register Volume 72, Number 17 (Friday, January 26, 2007)]
[Proposed Rules]
[Pages 3764-3768]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-1207]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27012; Directorate Identifier 2006-NM-188-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-601, A300 B4-603,
A300 B4-605R, A300 C4-605R Variant F, A310-204, A310-304, and A310-308
Airplanes Equipped With General Electric CF6-80C2 Engines
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 certain Airbus Model A300 B4-600, B4-
600R, C4-605R Variant F, and F4-600R (collectively called A300-600)
series airplanes; and Model A310 series airplanes. The existing AD
currently requires a one-time inspection for damage of the integrated
drive generator (IDG) electrical harness and pyramid arm, and repair if
necessary. This proposed AD would add new repetitive inspections,
which, when initiated, would terminate the inspection required by the
existing AD. This proposed AD would also require repairing damage and
protecting the harness. The proposed AD would also provide for optional
terminating action for the repetitive inspections. This proposed AD
also removes certain airplanes from the applicability of the existing
AD. This proposed AD results from a report of structural damage on the
forward pyramid arm of an engine pylon due to chafing of the IDG
electrical harness against the structure of the pyramid arm. We are
proposing this AD to prevent electrical arcing in the engine pylon,
which could result in loss of the relevant alternating current (AC) bus
bar, reduced structural integrity of the engine pylon, and possible
loss of control of the airplane.
DATES: We must receive comments on this proposed AD by February 26,
2007.
[[Page 3765]]
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: 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:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2007-27012; Directorate Identifier 2006-NM-188-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
On April 16, 2004, we issued AD 2004-09-01, amendment 39-13590 (69
FR 23090, April 28, 2004), for certain Airbus Model A300 B4-600, B4-
600R, C4-605R Variant F, and F4-600R (collectively called A300-600)
series airplanes; and Model A310 series airplanes. That AD requires a
one-time inspection for damage of the integrated drive generator (IDG)
electrical harness and pyramid arm, and repair if necessary. That AD
resulted from a report of structural damage on the forward pyramid arm
of an engine pylon during a scheduled maintenance check. Investigation
revealed that the damage was caused by chafing of the IDG electrical
harness against the structure of the pyramid arm. We issued that AD to
prevent electrical arcing within the engine pylon, which could result
in loss of the relevant alternating current (AC) bus bar, reduced
structural integrity of the engine pylon, and possible loss of control
of the airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2004-09-01 explains that we considered the
requirements ``interim action'' and were considering further
rulemaking. We have now determined that further rulemaking is
necessary, and this proposed AD follows from that determination. Since
we issued AD 2004-09-01, the European Aviation Safety Agency (EASA),
which is the airworthiness authority for the European Union, has
advised us that a repetitive inspection program is necessary to ensure
the functionality of the AC bus bar and the structural integrity of the
pylon.
Relevant Service Information
Airbus has issued the service bulletins identified in the following
table.
Service Bulletins
------------------------------------------------------------------------
Airbus Service
Actions Bulletin Affected model
------------------------------------------------------------------------
Inspection (repetitive A300-24-6097, dated A300-600 series
inspections of the IDG March 3, 2006, airplanes.
electrical harness and including Appendix
pylon forward pyramid 01.
arms), and protection of
the harness.
A310-24-2100, dated A310 series
March 3, 2006, airplanes.
including Appendix
01.
Modification (replacement of A300-54-6038, dated A300-600 series
the bracket feeder on the May 12, 2006. airplanes.
pylons).
A310-54-2039, dated A310 series
May 12, 2006. airplanes.
------------------------------------------------------------------------
Service Bulletins A300-24-6097 and A310-24-2100 describe procedures
for:
Doing a detailed visual inspection for wear on the pyramid
arms;
Repairing wear that is within certain limits;
Contacting Airbus for repair instructions if the wear
exceeds those limits;
Doing a detailed visual inspection of the cables;
Repairing damaged cables;
Protecting the harness, including installing adhesive
tape, lacing tape, and adhesive sealant; and
Reporting inspection results to Airbus.
The modification described in Service Bulletins A300-54-6038 and
A310-54-2039 eliminates the need for the repetitive inspections
specified above.
Accomplishing the actions specified in Service Bulletins A300-24-
6097 and A310-24-2100 is intended to adequately address the unsafe
condition. The EASA mandated that service information and issued
airworthiness directive 2006-0155,
[[Page 3766]]
dated June 1, 2006, to ensure the continued airworthiness of these
airplanes in the European Union. EASA airworthiness directive 2006-0155
superseded French airworthiness directive F-2004-039 (referenced in FAA
AD 2004-09-01). The EASA provided for the bracket feeder replacement as
optional terminating action to the repetitive inspections.
FAA's Determination and Requirements of the Proposed AD
These airplane models 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 we need to
issue an AD for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would:
Supersede AD 2004-09-01;
Retain the requirements of AD 2004-09-01;
Require new repetitive inspections for damage of the IDG
electrical harness and pylon forward pyramid arms, which, when
initiated, would terminate the inspection required by AD 2004-09-01;
Require repairing damage and protecting the harness;
Provide for optional terminating action for the repetitive
inspections;
Remove certain airplanes (including certain Model A300-600
and Model A310 series airplanes and those modified in production) from
the applicability of AD 2004-09-01; and
Require sending the inspection results to Airbus for each
repetitive inspection.
Differences Between Proposed AD and Service Information/EASA
Airworthiness Directive
The applicability of EASA airworthiness directive 2006-0155
excludes airplanes on which the actions specified in Airbus Service
Bulletin A300-54-6038 or A310-54-2039 have been done in service.
However, we have not excluded those airplanes in the applicability of
this proposed AD; rather, this proposed AD would provide for that
modification as an option to the required repetitive inspections.
Including these actions would ensure that the repetitive inspections
would continue on all affected airplanes until accomplishment of the
modification would allow the inspections to be terminated. Operators
must continue to operate the airplane in the configuration required by
this proposed AD unless an alternative method of compliance is
approved.
Service Bulletins A300-24-6097 and A310-24-2100 specify to contact
the manufacturer for instructions on how to repair certain conditions,
but paragraph (k) of this proposed AD would require repairing those
conditions using a method approved by the FAA or the EASA (or its
delegated agent). In light of the type of repair that would be required
to address the unsafe condition, and consistent with existing bilateral
airworthiness agreements, we have determined that, for this proposed
AD, a repair approved by either the FAA or the EASA would be acceptable
for compliance with paragraph (k) of this proposed AD.
Clarification of Inspection Terminology
The ``detailed visual inspection'' specified in Service Bulletins
A300-24-6097 and A310-24-2100 is referred to as a ``detailed
inspection'' in this proposed AD. Note 1 in this proposed AD identifies
a detailed inspection.
Explanation of Changes Made to Requirements of Existing AD
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved
alternative method of compliance (AMOC) on any airplane to which the
AMOC applies.
Paragraph (e) of the existing AD specifies repairing certain
discrepancies using a method approved by either the FAA or the
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its
delegated agent). The EASA has assumed responsibility for the airplane
models that would be subject to this AD. Therefore, we have revised
corresponding paragraph (i) in this proposed AD to specify the repair
of those discrepancies before the effective date of the new AD using a
method approved by the FAA, the DGAC (or its delegated agent), or the
EASA (or its delegated agent). After the effective date, paragraph (i)
of this proposed AD specifies the repair using a method approved by the
FAA or the EASA (or its delegated agent).
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average
Action Work hours labor rate Cost of Cost per airplane Number of U.S.- Fleet cost
per hour parts registered airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
One-time inspection (from AD 2004-09- 2 $80 $0 $160.................... 100.................... $16,000.
01).
Repetitive inspections and harness 4 80 0 $320, per inspection 100.................... $32,000, per inspection
protection (new proposed cycle. cycle.
requirement).
New optional modification............ 8 80 2,460 $3,100.................. Up to 100.............. Up to $310,000.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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
[[Page 3767]]
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 39-13590 (69 FR 23090, April 28, 2004) and adding
the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2007-27012; Directorate Identifier 2006-NM-
188-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by February
26, 2007.
Affected ADs
(b) This AD supersedes AD 2004-09-01.
Applicability
(c) This AD applies to Airbus Model A300 B4-601, A300 B4-603,
A300 B4-605R, A300 C4-605R Variant F, A310-204, A310-304, and A310-
308 airplanes; certificated in any category; equipped with General
Electric CF6-80C2 engines without full-authority digital electronic
control (FADEC); excluding airplanes on which Airbus Modification
13184 was done in production.
Unsafe Condition
(d) This AD results from a report of structural damage on the
forward pyramid arm of an engine pylon due to chafing of the
integrated drive generator (IDG) electrical harness against the
structure of the pyramid arm. We are issuing this AD to prevent
electrical arcing in the engine pylon, which could result in loss of
the relevant alternating current (AC) bus bar, reduced structural
integrity of the engine pylon, and possible loss of control of the
airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD 2004-09-01
All Operators Telex Reference
(f) The term ``All Operators Telex,'' or ``AOT,'' as used in
paragraphs (g), (h), and (j) of this AD, means the following AOTs,
as applicable:
(1) For Model A300 B4-601, A300 B4-603, A300 B4-605R, and A300
C4-605R Variant F airplanes: Airbus AOT A300-54A6037, dated February
19, 2004; and
(2) For Model A310-204, A310-304, and -308 airplanes: Airbus AOT
A310-54A2038, dated February 19, 2004.
Inspection
(g) At the applicable time in paragraph (g)(1) or (g)(2) of this
AD, do a one-time detailed inspection for discrepancies of the IDG
harness, harness bracket, retaining fasteners, and pyramid arm, in
accordance with the applicable AOT.
(1) For airplanes on which Airbus Modification 07591 has not
been incorporated as of May 13, 2004 (the effective date of AD 2004-
09-01): Within 10 days after May 13, 2004.
(2) For airplanes on which Airbus Modification 07591 has been
incorporated as of May 13, 2004: Within 600 flight hours after May
13, 2004.
Note 1: 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.''
Related Investigative and Corrective Actions for Damaged Electrical
Harness
(h) If any discrepancy in the IDG electrical harness, fretting
at the convoluted conduits, or contact between the IDG electrical
harness and the pyramid arms is found during the inspection required
by paragraph (g) of this AD: Before further flight, do the
applicable related investigative actions and corrective actions in
accordance with the applicable AOT.
Corrective Action for Damaged Electrical Harness Bracket, Retaining
Fasteners, or Pyramid Arm
(i) If any discrepancy in the electrical harness bracket,
retaining fasteners, or pyramid arm is found during the inspection
required by paragraph (g) of this AD: Before further flight, repair
in accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
agent); or the European Aviation Safety Agency (EASA) (or its
delegated agent). After the effective date of this AD, repair in
accordance with a method approved by the FAA or the EASA.
No Reporting Requirement for Paragraph (g) of This AD
(j) Although the referenced AOTs describe procedures for
submitting certain information to the manufacturer, no report is
required for the inspection required by paragraph (g) of this AD.
New Requirements of This AD
Repetitive Inspections
(k) Within 6 months after the effective date of this AD, and
thereafter at intervals not to exceed 12 months: Do a detailed
inspection for damage of the IDG harness and the pylon pyramid arms,
and protect the harness. Do the actions in accordance with Airbus
Service Bulletin A300-24-6097, dated March 3, 2006 (for Model A300
B4-601, A300 B4-603, A300 B4-605R, and A300 C4-605R Variant F
airplanes); or A310-24-2100, dated March 3, 2006 (for Model A310-
204, A310-304, and A310-308 airplanes). The initial inspection
terminates the requirements of paragraph (g) of this AD. If any
discrepancy is found: Before further flight, repair in accordance
with the applicable service bulletin; except, where the service
bulletin specifies to contact the manufacturer for repair
instructions, this AD requires repair using a method approved by
either the Manager, International Branch, ANM-116; or the EASA (or
its delegated agent).
Report
(l) At the applicable times specified in paragraphs (l)(1) and
(l)(2) of this AD, submit a report of the findings (both positive
and negative) of each inspection required by paragraph (k) of this
AD. Send the report to Airbus Customer Services Directorate,
Department AI/SE-E43, 1 Rond Point
[[Page 3768]]
Maurice Bellonte, 31707 Blagnac, Cedex, France. The report must
include the information specified in Appendix 01 of Airbus Service
Bulletin A300-24-6097 or A310-24-2100, both dated March 3, 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) For each inspection done after the effective date of this
AD: Send the report within 30 days after the inspection.
(2) If an inspection was done before the effective date of this
AD: Send the report within 30 days after the effective date of this
AD.
Optional Terminating Action
(m) Replacement of the bracket feeder on the pylons terminates
the requirements of this AD if the bracket feeder is replaced in
accordance with Airbus Service Bulletin A300-54-6038, dated May 12,
2006 (for Model A300 B4-601, A300 B4-603, A300 B4-605R, and A300 C4-
605R Variant F airplanes); or A310-54-2039, dated May 12, 2006 (for
Model A310-204, A310-304, and A310-308 airplanes); as applicable.
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) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(o) EASA airworthiness directive 2006-0155, dated June 1, 2006,
also addresses the subject of this AD.
Issued in Renton, Washington, on December 26, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-1207 Filed 1-25-07; 8:45 am]
BILLING CODE 4910-13-P
