Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 33658-33661 [E6-9062]
Download as PDF
33658
Proposed Rules
Federal Register
Vol. 71, No. 112
Monday, June 12, 2006
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA 2006–24983; Directorate
Identifier 2005–NM–196–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320, and A321 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
wwhite on PROD1PC61 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Airbus
Model A318, A319, A320, and A321
airplanes. The existing AD currently
requires a one-time inspection to
determine the serial number of both
main landing gear (MLG) sliding tubes,
repetitive detailed inspections for
cracking of the affected MLG sliding
tubes, and corrective actions if
necessary. This proposed AD would
retain these inspections and add new
repetitive inspections for cracking of the
MLG sliding tubes. This proposed AD
would also require eventual
replacement of both MLG shock
absorbers. Doing this replacement
would terminate the repetitive
inspection requirements of this
proposed AD. This proposed AD results
from a determination that additional
inspections and mandatory replacement
of the MLG shock absorbers are
necessary. We are proposing this AD to
detect and correct cracking in an MLG
sliding tube, which could result in
failure of the sliding tube, loss of one
axle, and consequent reduced
controllability of the airplane.
DATES: We must receive comments on
this proposed AD by July 12, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
VerDate Aug<31>2005
20:57 Jun 09, 2006
Jkt 208001
• 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
Dulin, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; 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–2006–24983;
Directorate Identifier 2005–NM–196–
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
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
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 May 28, 2004, we issued AD
2004–11–13, amendment 39–13659 (69
FR 31867, June 8, 2004), for all Airbus
Model A318, A319, A320, and A321
airplanes. That AD currently requires a
one-time inspection to determine the
serial number (S/N) of both main
landing gear (MLG) sliding tubes,
repetitive inspections for cracking of the
MLG sliding tubes, and corrective
actions if necessary. That AD resulted
from a report that a linear crack was
found in a MLG sliding tube at the
intersection of the cylinder and the axle
due to a non-metallic inclusion in the
base metal, and another report that the
number of MLG sliding tubes subject to
the identified unsafe condition had
expanded. We issued that AD to detect
and correct cracking in an MLG sliding
tube, which could result in failure of the
sliding tube, loss of one axle, and
consequent reduced controllability of
the airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2004–11–13
specified that we considered the
requirements ‘‘interim action’’ and that
the manufacturer was developing a
modification to address the unsafe
condition. That AD explained that we
may consider further rulemaking if a
modification is developed, approved,
and available. We have now determined
that additional detailed inspections and
magnetic particle inspections (MPI) and
eventual sliding tube replacement are
necessary to ensure safe operation and
has issued revised service information.
Therefore, we have determined that
further rulemaking is indeed necessary;
E:\FR\FM\12JNP1.SGM
12JNP1
Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Proposed Rules
this proposed AD follows from that
determination.
Relevant Service Information
Airbus has issued Service Bulletin
A320–32A1273, Revision 02, including
Appendix 01; dated May 26, 2005, to
replace All Operators Telex (AOT)
32A1273, Revision 01, dated May 6,
2004. (AD 2004–11–13 refers to
Revision 01 of the AOT as the
appropriate source of service
information for certain actions.) The
service bulletin retains the one-time
general visual inspection to determine
the S/N of both MLG sliding tubes and
the repetitive detailed inspections for
cracking of the sliding tube of the MLG
shock absorber described by the AOT.
The service bulletin also describes
procedures for new repetitive detailed
inspections and new MPIs of the sliding
tube, and eventual replacement of both
MLG shock absorbers with new or
serviceable MLG shock absorbers
equipped with sliding tubes having S/
Ns not listed in the service information.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition.
The service bulletin refers to MessierDowty Service Bulletins 201–32–43,
Revision 1 (for Airbus Model A321
airplanes), and 200–32–286, Revision 1
(for Airbus Model A318, A319, and
A320 airplanes); both dated May 1,
2005, as additional sources of service
information for accomplishing the
detailed inspections and MPIs.
´ ´
The Direction Generale de l’Aviation
Civile (DGAC) mandated the service
information and issued French
airworthiness directive F–2005–115,
dated July 6, 2005, to ensure the
continued airworthiness of these
airplanes in France. French
airworthiness directive F–2005–115
replaces French airworthiness directive
UF–2004–065, dated May 11, 2004,
which was referenced in AD 2004–11–
13.
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. Pursuant to this bilateral
airworthiness agreement, the DGAC has
kept the FAA informed of the situation
described above. We have examined the
DGAC’s findings, evaluated all pertinent
information, and determined that AD
action is necessary for airplanes of this
type design that are certificated for
operation in the United States.
This proposed AD would supersede
AD 2004–11–13 and would continue to
require a one-time general visual
inspection to determine the S/N of both
MLG sliding tubes and the repetitive
detailed inspections for cracking of the
sliding tube of the MLG shock absorber.
This proposed AD would also require
accomplishing the actions specified in
33659
Airbus Service Bulletin A320–32A1273,
Revision 02, described previously.
Changes to Existing AD
Due to the new requirements of this
proposed AD, paragraphs (h), (i), and (j)
of AD 2004–11–13 have been revised as
applicable and incorporated as new
paragraphs (l), (m), and (n) of this
proposed AD.
Clarification of Inspection Terminology
In this proposed AD, the ‘‘detailed
visual inspection’’ specified in French
airworthiness directive F–2005–115 is
referred to as a ‘‘detailed inspection.’’
We have included the definition for a
detailed inspection in a note in the
proposed AD.
Costs of Compliance
This proposed AD would affect about
720 airplanes of U.S. registry. The
following table provides the estimated
costs for U.S. operators to comply with
this proposed AD at an estimated cost
of $80 per work hour. Operators should
note that, although all U.S.-registered
airplanes are subject to the requirements
of the existing AD, there are only 297
possible affected MLG sliding tubes in
the worldwide fleet. We have no way of
knowing how many affected MLG
sliding tubes, if any, are installed in
U.S.-registered airplanes. Therefore, the
estimated costs to perform the new
requirements of this proposed AD apply
only to individual sliding tubes; no fleet
cost can be determined for these actions.
ESTIMATED COSTS TO PERFORM REQUIREMENTS OF EXISTING AD 2004–11–13
Action
Work
hours
Parts
Cost per
airplane
Fleet cost
General visual inspection to determine serial number ....................................................
1
None ........
$80
$57,600
ESTIMATED COSTS TO PERFORM NEW REQUIREMENTS OF THIS PROPOSED AD
Action
Work
hours
Parts
Cost per sliding tube
Detailed inspection ...............................................................................................
Detailed inspection and MPI .................................................................................
1
9
None ............................
None ............................
Replacement of sliding tube. ................................................................................
8
$38,278 to $45,310 .....
$80, per inspection cycle.
$720, per inspection
cycle.
$39,918 to $45,950
wwhite on PROD1PC61 with PROPOSALS
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.
VerDate Aug<31>2005
20:57 Jun 09, 2006
Jkt 208001
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
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
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
E:\FR\FM\12JNP1.SGM
12JNP1
33660
Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Proposed Rules
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13659 (69
FR 31867, June 8, 2004) and adding the
following new airworthiness directive
(AD):
Airbus: Docket No. FAA–2006–24983;
Directorate Identifier 2005–NM–196–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by July 12, 2006.
wwhite on PROD1PC61 with PROPOSALS
Affected ADs
(b) This AD supersedes AD 2004–11–13.
Applicability
(c) This AD applies to all Airbus Model
A318, A319, A320, and A321 airplanes,
certificated in any category.
Unsafe Condition
(d) This AD results from a determination
that additional inspections and mandatory
replacement of the MLG shock absorbers are
necessary. We are issuing this AD to detect
and correct cracking in an MLG sliding tube,
VerDate Aug<31>2005
20:57 Jun 09, 2006
Jkt 208001
which could result in failure of the sliding
tube, loss of one axle, 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.
Service Information References
(f) The term ‘‘service information,’’ as used
in this AD, means Airbus All Operators Telex
(AOT) A320–32A1273, Revision 01, dated
May 6, 2004; or the Accomplishment
Instructions of Airbus Service Bulletin A320–
32A1273, Revision 02, including Appendix
01, dated May 26, 2005. After the effective
date of this AD, only Airbus Service Bulletin
A320–32A1273, Revision 02, may be used.
Note 1: Airbus AOT A320–32A1273,
Revision 01, and Airbus Service Bulletin
A320–32A1273, Revision 02, refer to
Messier-Dowty Service Bulletins 201–32–43
and 200–32–286, both currently at Revision
1, dated May 1, 2005, as additional sources
of service information for accomplishing the
detailed inspections and magnetic particle
inspections (MPI).
Restatement of Certain Requirements of AD
2004–11–13
Serial Number (S/N) Identification
(g) For all airplanes: Within 30 days after
June 23, 2004 (the effective date of AD 2004–
11–13), do a one-time general visual
inspection to determine the S/N of both MLG
sliding tubes, in accordance with the service
information. Instead of inspecting the MLG
sliding tubes, reviewing the airplane
maintenance records is acceptable if the S/N
of the MLG sliding tubes can be positively
determined from that review.
(1) If the S/N of the MLG sliding tube is
not listed in the service information: No
further action is required by this paragraph
for that sliding tube.
(2) If the S/N of the MLG sliding tube is
listed in the service information: Do the
actions in paragraph (g)(2)(i) or (g)(2)(ii) of
this AD, as applicable.
(i) For any MLG not inspected before June
23, 2004: Before further flight, do a detailed
inspection of the MLG for cracking in
accordance with the service information.
(A) If no cracking is found in any MLG
sliding tube: Repeat the detailed inspection
thereafter at intervals not to exceed 10 days,
until the MLG replacement specified by
paragraph (g)(2)(i)(B), (h), or (i) of this AD has
been accomplished.
(B) If any cracking is found in any MLG
sliding tube: Before further flight replace the
part with a new or serviceable part in
accordance with a method approved by
either the FAA or the Direction Generale de
l’Aviation Civile (DGAC) (or its delegated
agent). Chapter 32 of the Airbus A318/A319/
A320/A321 Aircraft Maintenance Manual
(AMM) is one approved method. Installing an
MLG sliding tube having an S/N that is not
listed in the service information terminates
the repetitive inspections required by
paragraph (h) of this AD for that MLG sliding
tube only.
(ii) For any MLG that has been inspected
before June 23, 2004: Within 10 days after
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
that inspection, do the detailed inspection
required by paragraph (g)(2)(i) of this AD.
New Requirements of This AD
Detailed Inspection and MPI
(h) For any airplane equipped with any
MLG having a sliding tube installed that is
identified with a S/N listed in the service
information: Within 500 flight cycles after
the effective date of this AD, perform a
detailed inspection and an MPI of the MLG
sliding tube for cracking in accordance with
the service information. Repeat these
inspections thereafter at intervals not to
exceed 1,200 flight cycles until paragraph (i)
of this AD has been accomplished. If any
cracking is discovered during any inspection
required by this paragraph, before further
flight, replace the cracked sliding tube with
a new or serviceable sliding tube in
accordance with the service information.
Replacing the MLG sliding tube with a
sliding tube having a S/N not listed in the
service information terminates the repetitive
inspection requirements of this paragraph
and paragraph (g)(2)(i)(A) of this AD for that
sliding tube only.
Terminating Action
(i) Within 41 months after the effective
date of this AD, replace all MLG shock
absorbers equipped with sliding tubes having
S/Ns listed in the service information with
new or serviceable MLG shock absorbers
equipped with sliding tubes having S/Ns not
listed in the service information, using a
method approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the DGAC (or
its delegated agent). Chapter 32, page block
401, of the Airbus A318/A319/A320/A321
AMM is one approved method. Replacing the
MLG shock absorbers in accordance with this
paragraph terminates all repetitive
inspections required by this AD.
Submission of Cracked Parts Not Required
(j) The service information has instructions
to send any cracked part to Messier-Dowty.
This AD does not include such a
requirement.
Reporting Requirement
(k) Prepare a report of any crack found
during any inspection required by paragraph
(g) or (h) of this AD. Submit the report to
Airbus Customer Services, Engineering and
Technical Support, Attention: M.Y. Quimiou,
SEE33, fax +33+ (0) 5.6193.32.73, at the
applicable time specified in paragraph (k)(1)
or (k)(2) of this AD. The report must include
the MLG sliding tube P/N and S/N, date of
inspection, a description of any cracking
found, the airplane serial number, and the
number of flight cycles on the MLG at the
time of inspection. Under the provisions of
the Paperwork Reduction Act of 1980 (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 any inspection done after June 23,
2004, but before the effective date of this AD:
Within 30 days after the inspection or 30
days after the effective date of this AD,
whichever comes first.
E:\FR\FM\12JNP1.SGM
12JNP1
Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Proposed Rules
(2) For any inspection done after the
effective date of this AD: Within 30 days after
the inspection.
Parts Installation
(l) As of the effective date of this AD, no
person may install, on any airplane, any
sliding tube, or MLG shock absorber having
a sliding tube installed, if the sliding tube has
a S/N identified in the service information,
unless the sliding tube has been inspected,
and any applicable corrective actions have
been done, in accordance with paragraph
(g)(2)(i), (h), or (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested using 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
(n) French airworthiness directive F–2005–
115, dated July 6, 2005, also addresses the
subject of this AD.
Issued in Renton, Washington, on May 31,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–9062 Filed 6–9–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24990; Directorate
Identifier 2006–NM–013–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A319, A320, and A321 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
wwhite on PROD1PC61 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Airbus Model A319, A320, and
A321 airplanes. This proposed AD
would require an inspection to
determine if the stiff part of the girt and
girt bar position of the forward left-hand
and right-hand passenger doors is
incorrect, and repair if necessary. This
proposed AD results from cases of girt
bar disengagement from the floor fitting
during deployment tests of slide rafts at
the forward passenger doors. We are
proposing this AD to prevent
VerDate Aug<31>2005
20:57 Jun 09, 2006
Jkt 208001
disengagement of the telescopic girt bar
from the airplane when the door is
opened in emergency situations, which
could result in the inability to open the
passenger door and to use the escape
slide/raft at that door during an
emergency evacuation of the airplane.
DATES: We must receive comments on
this proposed AD by July 12, 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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
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 ‘‘FAA–2006–24990; Directorate
Identifier 2006–NM–013–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
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
33661
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
´ ´
The Direction Generale de l’Aviation
Civile (DGAC), which is the
airworthiness authority for France,
notified us that an unsafe condition may
exist on certain Airbus Model A319,
A320, and A321 airplanes. The DGAC
advises that, during deployment tests of
slide rafts at the forward passenger
doors, cases of girt bar disengagement
from the floor fitting were reported.
Investigations have demonstrated that
the girt bar disengagements were due to
incorrect position of the stiff part of the
girt bar during installation of the slide
raft on airplanes. This may cause
inboard-directed loads on the girt bar,
preventing a correct engagement in the
floor fittings. This condition, if not
corrected, could result in disengagement
of the telescopic girt bar from the
airplane when the door is opened in
emergency situations, which could
result in the inability to open the
passenger door and to use the escape
slide/raft at that door during an
emergency evacuation of the airplane.
Relevant Service Information
Airbus has issued Service Bulletin
A320–25–1394, Revision 01, dated
December 12, 2005. The service bulletin
describes procedures for a general visual
inspection to determine whether the
stiff part of the girt and girt bar position
of the forward left-hand and right-hand
passenger doors is incorrect, and repair
if necessary. Accomplishing the actions
specified in the service information is
intended to adequately address the
unsafe condition. The DGAC mandated
the service information and issued
French airworthiness directive F–2005–
E:\FR\FM\12JNP1.SGM
12JNP1
Agencies
[Federal Register Volume 71, Number 112 (Monday, June 12, 2006)]
[Proposed Rules]
[Pages 33658-33661]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-9062]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 /
Proposed Rules
[[Page 33658]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA 2006-24983; Directorate Identifier 2005-NM-196-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320, and A321
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 A318, A319, A320, and
A321 airplanes. The existing AD currently requires a one-time
inspection to determine the serial number of both main landing gear
(MLG) sliding tubes, repetitive detailed inspections for cracking of
the affected MLG sliding tubes, and corrective actions if necessary.
This proposed AD would retain these inspections and add new repetitive
inspections for cracking of the MLG sliding tubes. This proposed AD
would also require eventual replacement of both MLG shock absorbers.
Doing this replacement would terminate the repetitive inspection
requirements of this proposed AD. This proposed AD results from a
determination that additional inspections and mandatory replacement of
the MLG shock absorbers are necessary. We are proposing this AD to
detect and correct cracking in an MLG sliding tube, which could result
in failure of the sliding tube, loss of one axle, and consequent
reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by July 12, 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 Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; 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-2006-24983; Directorate Identifier 2005-NM-196-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 May 28, 2004, we issued AD 2004-11-13, amendment 39-13659 (69 FR
31867, June 8, 2004), for all Airbus Model A318, A319, A320, and A321
airplanes. That AD currently requires a one-time inspection to
determine the serial number (S/N) of both main landing gear (MLG)
sliding tubes, repetitive inspections for cracking of the MLG sliding
tubes, and corrective actions if necessary. That AD resulted from a
report that a linear crack was found in a MLG sliding tube at the
intersection of the cylinder and the axle due to a non-metallic
inclusion in the base metal, and another report that the number of MLG
sliding tubes subject to the identified unsafe condition had expanded.
We issued that AD to detect and correct cracking in an MLG sliding
tube, which could result in failure of the sliding tube, loss of one
axle, and consequent reduced controllability of the airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2004-11-13 specified that we considered the
requirements ``interim action'' and that the manufacturer was
developing a modification to address the unsafe condition. That AD
explained that we may consider further rulemaking if a modification is
developed, approved, and available. We have now determined that
additional detailed inspections and magnetic particle inspections (MPI)
and eventual sliding tube replacement are necessary to ensure safe
operation and has issued revised service information. Therefore, we
have determined that further rulemaking is indeed necessary;
[[Page 33659]]
this proposed AD follows from that determination.
Relevant Service Information
Airbus has issued Service Bulletin A320-32A1273, Revision 02,
including Appendix 01; dated May 26, 2005, to replace All Operators
Telex (AOT) 32A1273, Revision 01, dated May 6, 2004. (AD 2004-11-13
refers to Revision 01 of the AOT as the appropriate source of service
information for certain actions.) The service bulletin retains the one-
time general visual inspection to determine the S/N of both MLG sliding
tubes and the repetitive detailed inspections for cracking of the
sliding tube of the MLG shock absorber described by the AOT. The
service bulletin also describes procedures for new repetitive detailed
inspections and new MPIs of the sliding tube, and eventual replacement
of both MLG shock absorbers with new or serviceable MLG shock absorbers
equipped with sliding tubes having S/Ns not listed in the service
information. Accomplishing the actions specified in the service
information is intended to adequately address the unsafe condition.
The service bulletin refers to Messier-Dowty Service Bulletins 201-
32-43, Revision 1 (for Airbus Model A321 airplanes), and 200-32-286,
Revision 1 (for Airbus Model A318, A319, and A320 airplanes); both
dated May 1, 2005, as additional sources of service information for
accomplishing the detailed inspections and MPIs.
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC)
mandated the service information and issued French airworthiness
directive F-2005-115, dated July 6, 2005, to ensure the continued
airworthiness of these airplanes in France. French airworthiness
directive F-2005-115 replaces French airworthiness directive UF-2004-
065, dated May 11, 2004, which was referenced in AD 2004-11-13.
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. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 2004-11-13 and would continue
to require a one-time general visual inspection to determine the S/N of
both MLG sliding tubes and the repetitive detailed inspections for
cracking of the sliding tube of the MLG shock absorber. This proposed
AD would also require accomplishing the actions specified in Airbus
Service Bulletin A320-32A1273, Revision 02, described previously.
Changes to Existing AD
Due to the new requirements of this proposed AD, paragraphs (h),
(i), and (j) of AD 2004-11-13 have been revised as applicable and
incorporated as new paragraphs (l), (m), and (n) of this proposed AD.
Clarification of Inspection Terminology
In this proposed AD, the ``detailed visual inspection'' specified
in French airworthiness directive F-2005-115 is referred to as a
``detailed inspection.'' We have included the definition for a detailed
inspection in a note in the proposed AD.
Costs of Compliance
This proposed AD would affect about 720 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this proposed AD at an estimated cost of $80 per work hour.
Operators should note that, although all U.S.-registered airplanes are
subject to the requirements of the existing AD, there are only 297
possible affected MLG sliding tubes in the worldwide fleet. We have no
way of knowing how many affected MLG sliding tubes, if any, are
installed in U.S.-registered airplanes. Therefore, the estimated costs
to perform the new requirements of this proposed AD apply only to
individual sliding tubes; no fleet cost can be determined for these
actions.
Estimated Costs to Perform Requirements of Existing AD 2004-11-13
----------------------------------------------------------------------------------------------------------------
Work Cost per
Action hours Parts airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
General visual inspection to determine 1 None..................... $80 $57,600
serial number.
----------------------------------------------------------------------------------------------------------------
Estimated Costs to Perform New Requirements of This Proposed AD
----------------------------------------------------------------------------------------------------------------
Work
Action hours Parts Cost per sliding tube
----------------------------------------------------------------------------------------------------------------
Detailed inspection............. 1 None........................... $80, per inspection cycle.
Detailed inspection and MPI..... 9 None........................... $720, per inspection cycle.
Replacement of sliding tube..... 8 $38,278 to $45,310............. $39,918 to $45,950
----------------------------------------------------------------------------------------------------------------
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
[[Page 33660]]
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 39-13659 (69 FR 31867, June 8, 2004) and adding the
following new airworthiness directive (AD):
Airbus: Docket No. FAA-2006-24983; Directorate Identifier 2005-NM-
196-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by July 12,
2006.
Affected ADs
(b) This AD supersedes AD 2004-11-13.
Applicability
(c) This AD applies to all Airbus Model A318, A319, A320, and
A321 airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a determination that additional
inspections and mandatory replacement of the MLG shock absorbers are
necessary. We are issuing this AD to detect and correct cracking in
an MLG sliding tube, which could result in failure of the sliding
tube, loss of one axle, 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.
Service Information References
(f) The term ``service information,'' as used in this AD, means
Airbus All Operators Telex (AOT) A320-32A1273, Revision 01, dated
May 6, 2004; or the Accomplishment Instructions of Airbus Service
Bulletin A320-32A1273, Revision 02, including Appendix 01, dated May
26, 2005. After the effective date of this AD, only Airbus Service
Bulletin A320-32A1273, Revision 02, may be used.
Note 1: Airbus AOT A320-32A1273, Revision 01, and Airbus Service
Bulletin A320-32A1273, Revision 02, refer to Messier-Dowty Service
Bulletins 201-32-43 and 200-32-286, both currently at Revision 1,
dated May 1, 2005, as additional sources of service information for
accomplishing the detailed inspections and magnetic particle
inspections (MPI).
Restatement of Certain Requirements of AD 2004-11-13
Serial Number (S/N) Identification
(g) For all airplanes: Within 30 days after June 23, 2004 (the
effective date of AD 2004-11-13), do a one-time general visual
inspection to determine the S/N of both MLG sliding tubes, in
accordance with the service information. Instead of inspecting the
MLG sliding tubes, reviewing the airplane maintenance records is
acceptable if the S/N of the MLG sliding tubes can be positively
determined from that review.
(1) If the S/N of the MLG sliding tube is not listed in the
service information: No further action is required by this paragraph
for that sliding tube.
(2) If the S/N of the MLG sliding tube is listed in the service
information: Do the actions in paragraph (g)(2)(i) or (g)(2)(ii) of
this AD, as applicable.
(i) For any MLG not inspected before June 23, 2004: Before
further flight, do a detailed inspection of the MLG for cracking in
accordance with the service information.
(A) If no cracking is found in any MLG sliding tube: Repeat the
detailed inspection thereafter at intervals not to exceed 10 days,
until the MLG replacement specified by paragraph (g)(2)(i)(B), (h),
or (i) of this AD has been accomplished.
(B) If any cracking is found in any MLG sliding tube: Before
further flight replace the part with a new or serviceable part in
accordance with a method approved by either the FAA or the Direction
Generale de l'Aviation Civile (DGAC) (or its delegated agent).
Chapter 32 of the Airbus A318/A319/A320/A321 Aircraft Maintenance
Manual (AMM) is one approved method. Installing an MLG sliding tube
having an S/N that is not listed in the service information
terminates the repetitive inspections required by paragraph (h) of
this AD for that MLG sliding tube only.
(ii) For any MLG that has been inspected before June 23, 2004:
Within 10 days after that inspection, do the detailed inspection
required by paragraph (g)(2)(i) of this AD.
New Requirements of This AD
Detailed Inspection and MPI
(h) For any airplane equipped with any MLG having a sliding tube
installed that is identified with a S/N listed in the service
information: Within 500 flight cycles after the effective date of
this AD, perform a detailed inspection and an MPI of the MLG sliding
tube for cracking in accordance with the service information. Repeat
these inspections thereafter at intervals not to exceed 1,200 flight
cycles until paragraph (i) of this AD has been accomplished. If any
cracking is discovered during any inspection required by this
paragraph, before further flight, replace the cracked sliding tube
with a new or serviceable sliding tube in accordance with the
service information. Replacing the MLG sliding tube with a sliding
tube having a S/N not listed in the service information terminates
the repetitive inspection requirements of this paragraph and
paragraph (g)(2)(i)(A) of this AD for that sliding tube only.
Terminating Action
(i) Within 41 months after the effective date of this AD,
replace all MLG shock absorbers equipped with sliding tubes having
S/Ns listed in the service information with new or serviceable MLG
shock absorbers equipped with sliding tubes having S/Ns not listed
in the service information, using a method approved by either the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the DGAC (or its delegated agent). Chapter 32,
page block 401, of the Airbus A318/A319/A320/A321 AMM is one
approved method. Replacing the MLG shock absorbers in accordance
with this paragraph terminates all repetitive inspections required
by this AD.
Submission of Cracked Parts Not Required
(j) The service information has instructions to send any cracked
part to Messier-Dowty. This AD does not include such a requirement.
Reporting Requirement
(k) Prepare a report of any crack found during any inspection
required by paragraph (g) or (h) of this AD. Submit the report to
Airbus Customer Services, Engineering and Technical Support,
Attention: M.Y. Quimiou, SEE33, fax +33+ (0) 5.6193.32.73, at the
applicable time specified in paragraph (k)(1) or (k)(2) of this AD.
The report must include the MLG sliding tube P/N and S/N, date of
inspection, a description of any cracking found, the airplane serial
number, and the number of flight cycles on the MLG at the time of
inspection. Under the provisions of the Paperwork Reduction Act of
1980 (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 any inspection done after June 23, 2004, but before the
effective date of this AD: Within 30 days after the inspection or 30
days after the effective date of this AD, whichever comes first.
[[Page 33661]]
(2) For any inspection done after the effective date of this AD:
Within 30 days after the inspection.
Parts Installation
(l) As of the effective date of this AD, no person may install,
on any airplane, any sliding tube, or MLG shock absorber having a
sliding tube installed, if the sliding tube has a S/N identified in
the service information, unless the sliding tube has been inspected,
and any applicable corrective actions have been done, in accordance
with paragraph (g)(2)(i), (h), or (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested using 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
(n) French airworthiness directive F-2005-115, dated July 6,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on May 31, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-9062 Filed 6-9-06; 8:45 am]
BILLING CODE 4910-13-P