Airworthiness Directives; Airbus Model A330, A340-200, and A340-300 Series Airplanes, 40942-40945 [E6-11417]
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40942
Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
BAE Systems (Operations) Limited
(Formerly British Aerospace Regional
Aircraft): Docket No. FAA–2006–25388;
Directorate Identifier 2006–NM–086–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by August 18, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems
(Operations) Limited Model BAe 146–100A,
–200A, and –300A series airplanes; and
Model Avro 146–RJ70A, 146–RJ85A, and
146–RJ100A airplanes; certificated in any
category; equipped with hydraulic
accumulators part number (P/N) AIR91666–
0, –1, or –2 installed.
Unsafe Condition
(d) This AD results from report that one
hydraulic accumulator failed in service,
which caused the loss of the yellow
hydraulic system when the airplane was
configured for landing. We are issuing this
AD to prevent damage to the pressure skin,
failure of certain hydraulic systems,
contamination of the cabin with hydraulic
mist, increased workload for the flightcrew
associated with the loss of one or more
hydraulic circuits, and consequent reduced
controllability of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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Inspection To Determine Serial Number
(f) Within 48 hours after the effective date
of this AD, inspect all P/N AIR91666–0, –1,
and –2 hydraulic accumulators to determine
whether any hydraulic accumulator is
installed that has a serial number (S/N)
identified in paragraph C of the
Accomplishment Instructions of BAE
Systems (Operations) Limited Service
Bulletin ISB.29–A046, dated March 14, 2006.
A review of airplane maintenance records is
acceptable in lieu of this inspection if the S/
N can be conclusively determined from that
review.
Replacement or Repetitive Inspections
(g) If any accumulator with an affected S/
N is identified during the inspection required
by paragraph (f) of this AD, do the action in
paragraph (g)(1) or (g)(2) of this AD. Do all
actions in accordance with the
Accomplishment Instructions of BAE
Systems (Operations) Limited Service
Bulletin ISB.29–A046, dated March 14, 2006,
except where the service bulletin specifies to
submit certain information to the
manufacturer, this AD does not include that
requirement.
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16:48 Jul 18, 2006
Jkt 208001
(1) Before further flight: Replace the
hydraulic accumulator with a new or
serviceable accumulator.
(2) Before further flight: Do a detailed
inspection for signs of failure (leaking or
cracking) of the hydraulic accumulator, and
replace any failed accumulator before further
flight. If there is no sign of failure, repeat the
inspection thereafter at the applicable
interval in paragraph (g)(2)(i) or (g)(2)(ii) of
this AD. Within 75 days after the effective
date of this AD, replace the affected
hydraulic accumulator with a new or
serviceable accumulator. Doing the
replacement terminates the repetitive
inspections.
(i) At intervals not to exceed 48 hours.
(ii) Before further flight following a report
of hydraulic fumes in the cabin air supply,
or after a hydraulic fluid low-level warning;
and thereafter at intervals not to exceed 48
hours.
(h) For airplanes on which more than one
affected accumulator is identified during the
inspection required by paragraph (f) of this
AD: Within 12 days after the effective date
of this AD, replace any affected accumulator
in accordance with paragraph (g)(1) of this
AD so that no more than one accumulator
with an affected S/N remains on the airplane;
and inspect any remaining accumulator at
the applicable interval in paragraph (g)(2) of
this AD.
Note 1: BAE Systems (Operations) Limited
Service Bulletin ISB.29–A046, dated March
14, 2006, refers to APPH Service Bulletin
AIR91666–29–02, dated March 2006, as an
additional source of service information for
determining if an accumulator is a
serviceable accumulator. The procedures
include disassembling the accumulator
cylinder, and testing it for cracking.
Note 2: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Parts Installation
(i) Except as provided by paragraph (g)(2)
of this AD: As of the effective date of this AD,
no hydraulic accumulator having P/N
AIR91666–0, –1, or –2 that has an S/N
identified in paragraph C of the
Accomplishment Instructions of BAE
Systems (Operations) Limited Service
Bulletin ISB.29–A046, dated March 14, 2006,
may be installed on any airplane except for
accumulators on which the actions specified
in the Accomplishment Instructions of APPH
Service Bulletin AIR91666–29–02, dated
March 2006, have been done.
Special Flight Permit Limited
(j) Using special flight permits (14 CFR
21.197 and 21.199) before all affected
hydraulic actuators are replaced on the
airplane is allowed only if the airplane has
not flown more than 5 flight cycles since the
last inspection done in accordance with
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paragraph (g)(2) or (h) of this AD, as
applicable; and if the flight can be
accomplished in one flight cycle with the
airplane unpressurized.
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, 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
(l) EASA emergency airworthiness
directive 2006–0061–E [Corrected], dated
March 17, 2006, also addresses the subject of
this AD.
Issued in Renton, Washington, on July 11,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–11415 Filed 7–18–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25389; Directorate
Identifier 2006–NM–059–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330, A340–200, and A340–300 Series
Airplanes
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 all Airbus
Model A330, A340–200, and A340–300
series airplanes. The existing AD
currently requires repetitive inspections
of a certain bracket that attaches the
flight deck instrument panel to the
airplane structure; replacement of the
bracket with a new, improved bracket;
and related investigative and corrective
actions if necessary. This proposed AD
would add a requirement for
replacement of the existing bracket with
a titanium-reinforced bracket, which
would end the repetitive inspections in
the existing AD. This proposed AD
would also require related investigative
and corrective actions while
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Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Proposed Rules
accomplishing the replacement, and
would reduce the applicability in the
existing AD. This proposed AD results
from a report of cracking damage found
on certain brackets that were replaced
per the requirements in the existing AD.
We are proposing this AD to prevent a
cracked bracket. Failure of this bracket,
combined with failure of the horizontal
beam, could result in collapse of the left
part of the flight deck instrument panel,
and consequent reduced controllability
of the airplane.
DATES: We must receive comments on
this proposed AD by August 18, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–2797; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘Docket No. FAA–2006–25389;
Directorate Identifier 2006–NM–059–
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
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16:48 Jul 18, 2006
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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 March 8, 2005, we issued AD
2005–06–08, amendment 39–14016 (70
FR 13345, March 21, 2005), for all
Airbus Model A330, A340–200, and
A340–300 series airplanes. That AD
requires repetitive inspections of a
certain bracket that attaches the flight
deck instrument panel to the airplane
structure; replacement of the bracket
with a new, improved bracket; and
related investigative and corrective
actions if necessary. That AD resulted
from reports of cracking of a certain
bracket that attaches the flight deck
instrument panel to the airplane
structure. We issued that AD to detect
and correct a cracked bracket. Failure of
this bracket, combined with failure of
the horizontal beam, could result in
collapse of the left part of the flight deck
instrument panel, and consequent
reduced controllability of the airplane.
Actions Since Existing AD Was Issued
Since AD 2005–06–08 was issued,
cracking damage found on certain
brackets that were replaced per the
requirements in the existing AD. In
addition, the preamble to AD 2005–06–
08 explained that we considered the
requirements ‘‘interim action’’ and were
considering further rulemaking. We now
have determined that further
rulemaking is indeed necessary, and
this proposed AD follows from that
determination.
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40943
Relevant Service Information
Airbus has issued Service Bulletins
A330–25–3227 and A340–25–4230, both
Revision 01, both dated May 3, 2005.
(The original issue of the service
bulletins was referenced as the
appropriate source of service
information for accomplishing the
actions in the existing AD.) Revision 01
of the service bulletins is essentially the
same as the original.
Airbus has also issued new Service
Bulletins A330–25–3249 and A340–25–
4245, both dated May 3, 2005. The
service bulletins describe procedures for
replacing the existing bracket that
attaches the flight deck instrument
panel to the airplane structure with a
titanium-reinforced bracket, and related
investigative and corrective actions if
necessary. The replacement eliminates
the need for the repetitive inspections.
The related investigative action includes
a detailed inspection for cracking of the
bracket; the corrective action includes a
detailed inspection of the horizontal
beam if two lugs are fully broken. The
service bulletins recommend contacting
Airbus for repair of cracking.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition.
The European Aviation Safety Agency
(EASA) mandated the service
information and issued airworthiness
directives 2006–0045 and 2006–0047,
both dated February 16, 2006, to ensure
the continued airworthiness of these
airplanes in the European Union.
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 products of this
type design that are certificated for
operation in the United States.
This proposed AD would supersede
AD 2005–06–08 and would retain
certain requirements of the existing AD;
however, the reporting requirement is
no longer necessary and is not retained
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Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Proposed Rules
in this proposed AD. This proposed AD
would also require accomplishing the
actions specified in the new service
information described previously,
except as discussed under ‘‘Differences
Between Proposed AD and EASA
Airworthiness Directives.’’
Differences Between Proposed AD and
EASA Airworthiness Directives
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The referenced EASA airworthiness
directives require contacting Airbus for
instructions on how to repair certain
conditions. This proposed AD requires
repairing those conditions using a
method that we or the EASA approve.
In light of the type of repair that would
be required to address the unsafe
condition, and consistent with existing
bilateral airworthiness agreements, we
have determined that, for this proposed
AD, a repair we or the EASA (or its
delegated agent) approve would be
acceptable for compliance with this
proposed AD.
In addition, the referenced EASA
airworthiness directives are not clear
regarding the requirement to replace not
only brackets having part number (P/N)
F2511012920000 but also brackets
having P/N F2511012920095 (the P/N
for the replacement bracket in the
existing AD). We have clarified that
brackets with the latter P/Ns must also
be replaced with titanium-reinforced
brackets having P/N F2511305220096,
since both of these brackets are
susceptible to eventual cracking
damage. Airbus Service Bulletins A330–
25–3227 and A340–25–4230 specify
replacing brackets having P/N
F2511012920000 with brackets having
P/N F2511012920095, and both P/Ns are
subject to repetitive inspection
requirements. The proposed AD clarifies
that both P/Ns would be required to be
replaced, as specified in paragraph (k) of
the new requirements.
Although the referenced EASA
airworthiness directives specify the
bracket location as ‘‘the left-hand
bracket,’’ this proposed AD does not
include that description. The part
numbers for affected brackets are
located only on the left-hand side of the
cockpit instrument panel; therefore, we
have used the term ‘‘certain brackets’’ to
be consistent with the language used in
the existing AD.
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.
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Costs of Compliance
This proposed AD would affect about
24 Model A330 series airplanes of U.S.
registry.
The inspections that are required by
AD 2005–06–08 and retained in this
proposed AD take about 1 work hour
per airplane, at an average labor rate of
$80 per work hour. Based on these
figures, the estimated cost of the
currently required actions is $80 per
airplane, per inspection cycle.
The new proposed replacement and
investigative actions would take about 9
work hours per airplane, at an average
labor rate of $80 per work hour.
Required parts would cost about $330
per airplane. Based on these figures, the
estimated cost of the new actions
specified in this proposed AD for U.S.
operators is $25,200, or $1,050 per
airplane.
There are currently no affected Model
A340–200 and –300 series airplanes of
U.S. registry. However, if one of these
airplanes is imported and put on the
U.S. Register in the future, these cost
estimates would also apply to those
airplanes.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
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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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14016 (70
FR 13345, March 21, 2005) and adding
the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2006–25389;
Directorate Identifier 2006–NM–059–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by August 18, 2006.
Affected ADs
(b) This AD supersedes AD 2005–06–08.
Applicability
(c) This AD applies to Airbus Model A330,
A340–200, and A340–300 series airplanes;
certificated in any category; except airplanes
on which Airbus Modification 53446 has
been incorporated in production.
Unsafe Condition
(d) This AD results from a report of
cracking damage found on certain brackets
that were replaced to address an unsafe
condition. We are issuing this AD to prevent
a cracked bracket. Failure of this bracket,
combined with failure of the horizontal
beam, could result in collapse of the left part
of the flight deck instrument panel, and
consequent reduced controllability of the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
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Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Proposed Rules
the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD
2005–06–08
Service Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Airbus Service Bulletins
A330–25–3227 (for Model A330 series
airplanes) and A340–25–4230 (for Model
A340–200 and –300 series airplanes), both
Revision 01, both dated May 3, 2005; as
applicable. Accomplishment before the
effective date of this AD of Airbus Service
Bulletins A330–25–3227 and A340–25–4230,
both including Appendix 01; both dated June
17, 2004; as applicable, is an acceptable
means of compliance for paragraphs (g), (h),
and (i) of this AD.
Initial Inspection
(g) At the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD, perform
a detailed inspection of the bracket having
part number (P/N) F2511012920000, which
attaches the flight deck instrument panel to
airplane structure, in accordance with the
service bulletin.
(1) For Model A330 series airplanes: Prior
to the accumulation of 16,500 total flight
cycles, or within 60 days after April 25, 2005
(the effective date of AD 2005–06–08),
whichever is later.
(2) For Model A340–200 and –300 series
airplanes: Prior to the accumulation of 9,700
total flight cycles, or within 2,700 flight
cycles after April 25, 2005, whichever is
later.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
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No Cracking/Repetitive Inspections
(h) If no crack is found during the initial
inspection required by paragraph (g) of this
AD: Repeat the inspection thereafter at the
applicable interval specified in paragraph
(h)(1) or (h)(2) of this AD, until the
replacement specified in paragraph (k) of this
AD has been accomplished.
(1) For Model A330 series airplanes:
Intervals not to exceed 13,800 flight cycles.
(2) For Model A340–200 and –300 series
airplanes: Intervals not to exceed 7,000 flight
cycles.
Crack Found/Replacement and Repetitive
Inspections
(i) If any crack is found during any
inspection required by paragraph (g) or (h) of
this AD: Do the actions in paragraphs (i)(1)
and (i)(2) of this AD, except as provided by
paragraph (j) of this AD, until
accomplishment of the replacement required
by paragraph (k) of this AD.
(1) Before further flight: Replace the
cracked bracket with a new, improved
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16:48 Jul 18, 2006
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bracket having P/N F2511012920095, in
accordance with the service bulletin.
(2) Repeat the inspection of the replaced
bracket as required by paragraph (g) of this
AD, at the time specified in paragraph (i)(2)(i)
or (i)(2)(ii) of this AD. Then, do repetitive
inspections or replace the bracket as
specified in paragraph (h) or (i) of this AD,
as applicable.
(i) For Model A330 series airplanes: Within
16,500 flight cycles after replacing the
bracket.
(ii) For Model A340–200 and –300 series
airplanes: Within 9,700 flight cycles after
replacing the bracket.
(j) If both flanges of a bracket are found
broken during any inspection required by
this AD: Before further flight, replace the
bracket as specified in paragraph (i) of this
AD and perform any applicable related
investigative and corrective actions (which
may include inspections for damage to
surrounding structure caused by the broken
bracket, and corrective actions for any
damage that is found), in accordance with a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent).
New Requirements of This AD
Replacement of Brackets/Investigative and
Corrective Actions
(k) Except as required by paragraph (i)(1)
of this AD: Within 72 months after the
effective date of this AD, replace existing
brackets having P/N F2511012920000 or P/N
F2511012920095 with titanium-reinforced
brackets having P/N F2511305220096; and
perform any related investigative and
corrective actions (which may include
detailed inspections for cracking of the
bracket or damage to surrounding structure
caused by a broken bracket, and applicable
corrective actions for any damage that is
found); in accordance with the service
bulletin. If any crack is found, before further
flight, repair in accordance with the service
bulletin. Replacement of the affected bracket
with a titanium-reinforced bracket having P/
N F2511305220096 ends the repetitive
inspections required by paragraph (h) or (i)
of this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
Related Information
(m) EASA airworthiness directives 2006–
0045 and 2006–0047, both dated February 16,
2006, also address the subject of this AD.
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40945
Issued in Renton, Washington, on July 11,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–11417 Filed 7–18–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25391; Directorate
Identifier 2006–NM–097–AD]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.28 Mark 0070 and 0100
Airplanes
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
Fokker Model F.28 Mark 0070 and 0100
airplanes. The existing AD currently
requires a one-time inspection of the
sliding members in the main landing
gear (MLG) for cracking and
replacement of the sliding members
with serviceable parts if necessary. This
proposed AD would require repetitive
magnetic particle inspections of the
sliding members of the MLG for
cracking and corrective actions as
necessary. This proposed AD results
from inspection findings that have
shown repetitive inspections are needed
to establish fleet safety. We are
proposing this AD to detect and correct
fatigue cracking of the sliding member,
which could result in possible
separation of the MLG from the airplane
and consequent reduced controllability
of the airplane upon landing and
possible injury to passengers.
DATES: We must receive comments on
this proposed AD by August 18, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
E:\FR\FM\19JYP1.SGM
19JYP1
]]>Agencies
[Federal Register Volume 71, Number 138 (Wednesday, July 19, 2006)]
[Proposed Rules]
[Pages 40942-40945]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-11417]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25389; Directorate Identifier 2006-NM-059-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330, A340-200, and A340-
300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Airbus Model A330, A340-200, and
A340-300 series airplanes. The existing AD currently requires
repetitive inspections of a certain bracket that attaches the flight
deck instrument panel to the airplane structure; replacement of the
bracket with a new, improved bracket; and related investigative and
corrective actions if necessary. This proposed AD would add a
requirement for replacement of the existing bracket with a titanium-
reinforced bracket, which would end the repetitive inspections in the
existing AD. This proposed AD would also require related investigative
and corrective actions while
[[Page 40943]]
accomplishing the replacement, and would reduce the applicability in
the existing AD. This proposed AD results from a report of cracking
damage found on certain brackets that were replaced per the
requirements in the existing AD. We are proposing this AD to prevent a
cracked bracket. Failure of this bracket, combined with failure of the
horizontal beam, could result in collapse of the left part of the
flight deck instrument panel, and consequent reduced controllability of
the airplane.
DATES: We must receive comments on this proposed AD by August 18, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2006-25389; Directorate Identifier 2006-NM-059-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 March 8, 2005, we issued AD 2005-06-08, amendment 39-14016 (70
FR 13345, March 21, 2005), for all Airbus Model A330, A340-200, and
A340-300 series airplanes. That AD requires repetitive inspections of a
certain bracket that attaches the flight deck instrument panel to the
airplane structure; replacement of the bracket with a new, improved
bracket; and related investigative and corrective actions if necessary.
That AD resulted from reports of cracking of a certain bracket that
attaches the flight deck instrument panel to the airplane structure. We
issued that AD to detect and correct a cracked bracket. Failure of this
bracket, combined with failure of the horizontal beam, could result in
collapse of the left part of the flight deck instrument panel, and
consequent reduced controllability of the airplane.
Actions Since Existing AD Was Issued
Since AD 2005-06-08 was issued, cracking damage found on certain
brackets that were replaced per the requirements in the existing AD. In
addition, the preamble to AD 2005-06-08 explained that we considered
the requirements ``interim action'' and were considering further
rulemaking. We now have determined that further rulemaking is indeed
necessary, and this proposed AD follows from that determination.
Relevant Service Information
Airbus has issued Service Bulletins A330-25-3227 and A340-25-4230,
both Revision 01, both dated May 3, 2005. (The original issue of the
service bulletins was referenced as the appropriate source of service
information for accomplishing the actions in the existing AD.) Revision
01 of the service bulletins is essentially the same as the original.
Airbus has also issued new Service Bulletins A330-25-3249 and A340-
25-4245, both dated May 3, 2005. The service bulletins describe
procedures for replacing the existing bracket that attaches the flight
deck instrument panel to the airplane structure with a titanium-
reinforced bracket, and related investigative and corrective actions if
necessary. The replacement eliminates the need for the repetitive
inspections. The related investigative action includes a detailed
inspection for cracking of the bracket; the corrective action includes
a detailed inspection of the horizontal beam if two lugs are fully
broken. The service bulletins recommend contacting Airbus for repair of
cracking. Accomplishing the actions specified in the service
information is intended to adequately address the unsafe condition.
The European Aviation Safety Agency (EASA) mandated the service
information and issued airworthiness directives 2006-0045 and 2006-
0047, both dated February 16, 2006, to ensure the continued
airworthiness of these airplanes in the European Union.
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 products of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 2005-06-08 and would retain
certain requirements of the existing AD; however, the reporting
requirement is no longer necessary and is not retained
[[Page 40944]]
in this proposed AD. This proposed AD would also require accomplishing
the actions specified in the new service information described
previously, except as discussed under ``Differences Between Proposed AD
and EASA Airworthiness Directives.''
Differences Between Proposed AD and EASA Airworthiness Directives
The referenced EASA airworthiness directives require contacting
Airbus for instructions on how to repair certain conditions. This
proposed AD requires repairing those conditions using a method that we
or the EASA approve. In light of the type of repair that would be
required to address the unsafe condition, and consistent with existing
bilateral airworthiness agreements, we have determined that, for this
proposed AD, a repair we or the EASA (or its delegated agent) approve
would be acceptable for compliance with this proposed AD.
In addition, the referenced EASA airworthiness directives are not
clear regarding the requirement to replace not only brackets having
part number (P/N) F2511012920000 but also brackets having P/N
F2511012920095 (the P/N for the replacement bracket in the existing
AD). We have clarified that brackets with the latter P/Ns must also be
replaced with titanium-reinforced brackets having P/N F2511305220096,
since both of these brackets are susceptible to eventual cracking
damage. Airbus Service Bulletins A330-25-3227 and A340-25-4230 specify
replacing brackets having P/N F2511012920000 with brackets having P/N
F2511012920095, and both P/Ns are subject to repetitive inspection
requirements. The proposed AD clarifies that both P/Ns would be
required to be replaced, as specified in paragraph (k) of the new
requirements.
Although the referenced EASA airworthiness directives specify the
bracket location as ``the left-hand bracket,'' this proposed AD does
not include that description. The part numbers for affected brackets
are located only on the left-hand side of the cockpit instrument panel;
therefore, we have used the term ``certain brackets'' to be consistent
with the language used in the existing AD.
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.
Costs of Compliance
This proposed AD would affect about 24 Model A330 series airplanes
of U.S. registry.
The inspections that are required by AD 2005-06-08 and retained in
this proposed AD take about 1 work hour per airplane, at an average
labor rate of $80 per work hour. Based on these figures, the estimated
cost of the currently required actions is $80 per airplane, per
inspection cycle.
The new proposed replacement and investigative actions would take
about 9 work hours per airplane, at an average labor rate of $80 per
work hour. Required parts would cost about $330 per airplane. Based on
these figures, the estimated cost of the new actions specified in this
proposed AD for U.S. operators is $25,200, or $1,050 per airplane.
There are currently no affected Model A340-200 and -300 series
airplanes of U.S. registry. However, if one of these airplanes is
imported and put on the U.S. Register in the future, these cost
estimates would also apply to those airplanes.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14016 (70 FR 13345, March 21, 2005) and adding
the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2006-25389; Directorate Identifier 2006-NM-
059-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by August
18, 2006.
Affected ADs
(b) This AD supersedes AD 2005-06-08.
Applicability
(c) This AD applies to Airbus Model A330, A340-200, and A340-300
series airplanes; certificated in any category; except airplanes on
which Airbus Modification 53446 has been incorporated in production.
Unsafe Condition
(d) This AD results from a report of cracking damage found on
certain brackets that were replaced to address an unsafe condition.
We are issuing this AD to prevent a cracked bracket. Failure of this
bracket, combined with failure of the horizontal beam, could result
in collapse of the left part of the flight deck instrument panel,
and consequent reduced controllability of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within
[[Page 40945]]
the compliance times specified, unless the actions have already been
done.
Restatement of Certain Requirements of AD 2005-06-08
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Airbus Service Bulletins A330-25-3227
(for Model A330 series airplanes) and A340-25-4230 (for Model A340-
200 and -300 series airplanes), both Revision 01, both dated May 3,
2005; as applicable. Accomplishment before the effective date of
this AD of Airbus Service Bulletins A330-25-3227 and A340-25-4230,
both including Appendix 01; both dated June 17, 2004; as applicable,
is an acceptable means of compliance for paragraphs (g), (h), and
(i) of this AD.
Initial Inspection
(g) At the applicable time specified in paragraph (g)(1) or
(g)(2) of this AD, perform a detailed inspection of the bracket
having part number (P/N) F2511012920000, which attaches the flight
deck instrument panel to airplane structure, in accordance with the
service bulletin.
(1) For Model A330 series airplanes: Prior to the accumulation
of 16,500 total flight cycles, or within 60 days after April 25,
2005 (the effective date of AD 2005-06-08), whichever is later.
(2) For Model A340-200 and -300 series airplanes: Prior to the
accumulation of 9,700 total flight cycles, or within 2,700 flight
cycles after April 25, 2005, whichever is later.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
No Cracking/Repetitive Inspections
(h) If no crack is found during the initial inspection required
by paragraph (g) of this AD: Repeat the inspection thereafter at the
applicable interval specified in paragraph (h)(1) or (h)(2) of this
AD, until the replacement specified in paragraph (k) of this AD has
been accomplished.
(1) For Model A330 series airplanes: Intervals not to exceed
13,800 flight cycles.
(2) For Model A340-200 and -300 series airplanes: Intervals not
to exceed 7,000 flight cycles.
Crack Found/Replacement and Repetitive Inspections
(i) If any crack is found during any inspection required by
paragraph (g) or (h) of this AD: Do the actions in paragraphs (i)(1)
and (i)(2) of this AD, except as provided by paragraph (j) of this
AD, until accomplishment of the replacement required by paragraph
(k) of this AD.
(1) Before further flight: Replace the cracked bracket with a
new, improved bracket having P/N F2511012920095, in accordance with
the service bulletin.
(2) Repeat the inspection of the replaced bracket as required by
paragraph (g) of this AD, at the time specified in paragraph
(i)(2)(i) or (i)(2)(ii) of this AD. Then, do repetitive inspections
or replace the bracket as specified in paragraph (h) or (i) of this
AD, as applicable.
(i) For Model A330 series airplanes: Within 16,500 flight cycles
after replacing the bracket.
(ii) For Model A340-200 and -300 series airplanes: Within 9,700
flight cycles after replacing the bracket.
(j) If both flanges of a bracket are found broken during any
inspection required by this AD: Before further flight, replace the
bracket as specified in paragraph (i) of this AD and perform any
applicable related investigative and corrective actions (which may
include inspections for damage to surrounding structure caused by
the broken bracket, and corrective actions for any damage that is
found), in accordance with a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA) (or its delegated
agent).
New Requirements of This AD
Replacement of Brackets/Investigative and Corrective Actions
(k) Except as required by paragraph (i)(1) of this AD: Within 72
months after the effective date of this AD, replace existing
brackets having P/N F2511012920000 or P/N F2511012920095 with
titanium-reinforced brackets having P/N F2511305220096; and perform
any related investigative and corrective actions (which may include
detailed inspections for cracking of the bracket or damage to
surrounding structure caused by a broken bracket, and applicable
corrective actions for any damage that is found); in accordance with
the service bulletin. If any crack is found, before further flight,
repair in accordance with the service bulletin. Replacement of the
affected bracket with a titanium-reinforced bracket having P/N
F2511305220096 ends the repetitive inspections required by paragraph
(h) or (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(m) EASA airworthiness directives 2006-0045 and 2006-0047, both
dated February 16, 2006, also address the subject of this AD.
Issued in Renton, Washington, on July 11, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-11417 Filed 7-18-06; 8:45 am]
BILLING CODE 4910-13-P
