Airworthiness Directives; Airbus Model A319-100, A320-200, and A321-100 and -200 Series Airplanes, 42005-42008 [05-14394]
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Federal Register / Vol. 70, No. 139 / Thursday, July 21, 2005 / Proposed Rules
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 FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Aerospatiale: Docket No. FAA–2005–21909;
Directorate Identifier 2005–NM–059–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
August 22, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Aerospatiale Model
ATR72–101, –102, –201, –202, –211, –212,
and –212A airplanes, certificated in any
category; except airplanes that have received
ATR Modification 5522 in production.
Unsafe Condition
(d) This AD was prompted by two reports
of rupture of the upper arm of the main
landing gear (MLG) secondary side brace
assembly due to fatigue cracking. We are
issuing this AD to prevent cracking of the
upper arms of the secondary side brace
assemblies of the MLG, which could result in
collapse of the MLG during takeoff or
landing, damage to the airplane, and possible
injury to the flightcrew and passengers.
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.
Inspections
(f) At the latest of the times specified in
paragraphs (f)(1), (f)(2), and (f)(3) of this AD:
Accomplish a general visual inspection for
contamination of the surface of the upper
arms of the MLG secondary side brace
assemblies, and an eddy current inspection
for cracking of the upper arms by doing all
the actions specified in Parts A and B of the
Accomplishment Instructions of MessierDowty Special Inspection Service Bulletin
631–32–178, Revision 1, dated September 30,
2004. Repeat the eddy current inspection at
intervals not to exceed 800 flight cycles until
accomplishment of paragraph (h) of this AD.
(1) Before the accumulation of 4,000 total
flight cycles on the secondary side brace.
(2) Before the accumulation of 800 flight
cycles on the secondary side brace since
overhauled.
(3) Within 200 flight cycles after the
effective date of this AD.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
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distance unless otherwise specified. A mirror
may be necessary to enhance visual access to
all exposed surfaces in the inspection area.
This level of inspection is made under
normally available lighting conditions such
as daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
Related Specified and Corrective Actions
(g) If any cracking is found during any
inspection required by paragraph (f) of this
AD: Before further flight, replace the affected
upper arm of the MLG secondary side brace
assembly as specified in paragraph (g)(1) or
(g)(2) of this AD.
(1) Replace the aluminum upper arm of the
MLG secondary side brace assembly with a
steel upper arm by doing the applicable
actions specified in the Accomplishment
Instructions of Messier-Dowty Service
Bulletin 631–32–183, dated October 6, 2004.
This replacement ends the repetitive
inspections required by paragraph (f) of this
AD for that side brace only.
(2) Replace the aluminum upper arm of the
MLG secondary side brace assembly with a
new or serviceable aluminum upper arm in
accordance with a method approved by
either the Manager, International Branch,
ANM–116, Transport Airplane Directorate,
´ ´
FAA; or the Direction Generale de l’Aviation
Civile (or its delegated agent). ATR
Component Maintenance Manual, Chapter
32–18–41, Revision 3, dated September 30,
2002, is one approved method. Accomplish
a general visual inspection for contamination
of the surface of the upper arm before the
accumulation of 4,000 total flight cycles on
the upper arm, and if cracks are found, before
further flight, replace the upper arm with a
steel upper arm as required by paragraph
(g)(1) of this AD. If no cracks are found,
repeat the eddy current inspection thereafter
at intervals not to exceed 800 flight cycles
until accomplishment of paragraph (h) of this
AD.
Terminating Action
(h) Replace all aluminum upper arms of
the MLG secondary side brace assembly with
steel upper arms by doing all the applicable
actions in accordance with the
Accomplishment Instructions of MessierDowty Service Bulletin 631–32–183, dated
October 6, 2004; at the applicable time
specified in paragraph (h)(1), (h)(2), (h)(3), or
(h)(4) of this AD. Accomplishing this
replacement ends the repetitive inspections
required by paragraph (f) of this AD.
(1) For airplanes on which any upper arm
has been overhauled before the effective date
of this AD and on which Messier-Bugatti
Service Bulletin 631–32–085, dated August
21, 1992, has not been accomplished, as of
the effective date of this AD: Within 15,000
flight cycles or 96 months, whichever is first,
since overhaul on the affected upper arm.
(2) For airplanes on which any upper arm
has been overhauled before the effective date
of this AD and on which Messier-Bugatti
Service Bulletin 631–32–085, dated August
21, 1992, has been accomplished, as of the
effective date of this AD: Within 18,000 flight
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42005
cycles or 96 months, whichever is first, since
overhaul on the affected upper arm.
(3) For airplanes on which any upper arm
has not been overhauled and on which
Messier-Bugatti Service Bulletin 631–32–085,
dated August 21, 1992, has not been
accomplished, as of the effective date of this
AD: Before the accumulation of 15,000 total
flight cycles on an upper arm since new, or
within 96 months on an upper arm since
new, whichever is first.
(4) For airplanes on which any upper arm
has not been overhauled and on which
Messier-Bugatti Service Bulletin 631–32–085,
dated August 21, 1992, has been
accomplished, as of the effective date of this
AD: Before the accumulation of 18,000 total
flight cycles on an upper arm since new, or
within 96 months on an upper arm since
new, whichever is first.
No Report Required
(i) Messier-Dowty Special Inspection
Service Bulletin 631–32–178, Revision 1,
dated September 30, 2004, recommends
sending an inspection report to MessierDowty, but this AD does not contain that
requirement.
Parts Installation
(j) As of the effective date of this AD, no
person may install, on any airplane, an
aluminum upper arm of the MLG secondary
side brace assembly, unless the applicable
requirements specified in paragraphs (f) and
(g) of this AD have been accomplished.
Alternative Methods of Compliance
(AMOCs)
(k) 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.
Related Information
(l) French airworthiness directive F–2004–
164, dated October 13, 2004, also addresses
the subject of this AD.
Issued in Renton, Washington, on July 14,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–14393 Filed 7–20–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19863; Directorate
Identifier 2003–NM–29–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A319–100, A320–200, and A321–100
and –200 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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Federal Register / Vol. 70, No. 139 / Thursday, July 21, 2005 / Proposed Rules
Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
ACTION:
SUMMARY: The FAA is revising an earlier
NPRM for an airworthiness directive
(AD) that applies to certain Airbus
Model A319–100, A320–200, and A321–
100 and –200 series airplanes. The
original NPRM would have superseded
an existing AD that currently requires
modification of the telescopic girt bar of
the escape slide/raft assembly, and
follow-on actions. The original NPRM
proposed to mandate a new
modification of the telescopic girt bar,
which would terminate the repetitive
functional tests required by the existing
AD. The original NPRM also proposed
to expand the applicability of the
existing AD. The original NPRM was
prompted by development of a new,
improved modification. This new action
would revise the original NPRM by
proposing to mandate the installation of
placards on the modified girt bars, and
reduce the compliance time. We are
proposing this supplemental NPRM to
prevent failure of the escape slide/raft to
deploy correctly, which could result in
the slide being unusable during an
emergency evacuation and consequent
injury to passengers or airplane
crewmembers.
We must receive comments on
this supplemental NPRM by August 15,
2005.
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.
For service information identified in
this proposed AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
DATES:
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the Nassif Building, Washington, DC.
This docket number is FAA–2004–
19863; the directorate identifier for this
docket is 2003–NM–29–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 proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2004–19863; Directorate Identifier
2003–NM–29–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this supplemental NPRM. We
will consider all comments received by
the closing date and may amend this
supplemental NPRM in light of those
comments.
We will post all comments submitted,
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 our docket 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 can review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you can visit
https://dms.dot.gov.
Examining the Docket
You can 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 ADDRESSES.
Comments will be available in the AD
docket shortly after the Docket
Management System (DMS) receives
them.
Discussion
We proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR
part 39) with a notice of proposed
rulemaking (NPRM) for an AD (the
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‘‘original NPRM’’) for certain Airbus
Model A319, A320, and A321 series
airplanes. The original NPRM proposed
to supersede AD 2001–16–14,
amendment 39–12383 (66 FR 42939,
August 16, 2001), which applies to
certain Airbus Model A319, A320, and
A321 series airplanes. The original
NPRM was published in the Federal
Register on December 16, 2004 (69 FR
75273). The original NPRM proposed to
retain the requirements of the existing
AD and mandate a new modification of
the telescopic girt bar, which would
terminate the repetitive functional tests
of the existing AD. The original NPRM
also proposed to expand the
applicability of the existing AD. The
original NPRM was prompted by
development of a new, improved
modification.
Comments
We have considered the following
comments on the original NPRM.
Request To Add Revised Service
Information
One commenter concurs with the
content of the original NPRM and asks
that Airbus Service Bulletins A320–52–
1112, Revision 03, dated June 27, 2003;
and Revision 04, dated November 12,
2003; be added as additional sources of
service information for accomplishing
the new modification. Revision 02 of the
service bulletin was referenced in the
original NPRM as the appropriate source
of service information for accomplishing
the modification of the telescopic girt
bar of the escape slide/raft assembly.
The commenter notes that Revisions 03
and 04 of the service bulletin did not
change the content of Revision 02 of the
service bulletin, and should be allowed
as an alternative method of compliance.
Another commenter asks that
Revision 05 of the referenced service
bulletin, dated June 25, 2004, be added
to the original NPRM as the source of
service information for accomplishing
the existing and new requirements. The
commenter notes that Revision 05 adds
procedures for the installation of a
sticker (placard) on each of the four girt
bars. That installation was omitted in
the procedures specified in previous
issues of the service bulletin. The
commenter adds that the purpose of the
stickers is to provide positive visual
indication of girt bar engagement in the
armed mode, and the Direction Generale
de l’Aviation Civile (DGAC), which is
the airworthiness authority for France,
is in the process of issuing a new
airworthiness directive to require
installation of those stickers.
We agree with the commenters.
Airbus has issued, and we have
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reviewed, Service Bulletins A320–52–
1112, Revision 03, dated June 27, 2003;
Revision 04, dated November 12, 2003;
and Revision 05, dated June 25, 2004.
No more work is necessary if Revisions
03 and 04 are used, as they are
essentially the same as Revision 02 of
the service bulletin. Revision 05 adds
procedures for installing placards on the
modified telescopic girt bars of the
escape slide/raft assembly.
The DGAC mandated compliance
with Revision 05 of the service bulletin
and issued French airworthiness
directive F–2005–057, dated April 13,
2005, to ensure the continued
airworthiness of these airplanes in
France.
We agree that the placards are needed
to provide positive visual indication of
girt bar engagement in the armed mode.
Therefore, we have changed paragraph
(g) of this supplemental NPRM to add
paragraphs (g)(1) and (g)(2), which
specify modifying the telescopic girt
bars and installing placards on the
modified girt bars using Revision 05 of
the service bulletin to accomplish those
actions. In addition, we have added
Revisions 03 and 04 to paragraph (i) of
this supplemental NPRM to give credit
for previous accomplishment of the
modification of the telescopic girt bar of
the escape slide/raft assembly.
Request for Excluding Installation of
Placards
One commenter asks that the
installation of placards recommended in
Revision 05 of the referenced service
bulletin be excluded from the
requirements of the original NPRM. The
commenter states that Revision 05
added procedures for installing a ‘‘dot’’
placard to the modified girt bar, for
identification. The commenter notes
that this placard seems to be selfsticking with adhesive, and does not
change the part number of the modified
girt bar. The commenter adds that the
placard will eventually come off and
cause compliance issues in the future,
even though there are currently no such
reports from Airbus. The commenter
also asks that references up to and
including Revision 05 of the service
bulletin be added to the original NPRM
as acceptable sources for the
instructions for the modification, with
the exception of the placard installation.
We do not agree with the commenter’s
request. We have determined that
installation of the placards, as identified
in Revision 05 of the service bulletin
and required by French airworthiness
directive F–2005–057, is necessary and
the placards should be maintained as
part of normal airplane maintenance. As
stated previously, the purpose of the
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stickers is to provide positive visual
indication of girt bar engagement in the
armed mode. This visual indication will
ensure continued safe flight of the
airplane. No change is made to the
supplemental NPRM in this regard.
Request To Reduce Compliance Time
The same commenter asks (as a
follow-on to its previous request) that
we reduce the compliance time for the
modification specified in paragraph (g)
of the original NPRM to ‘‘not later than
December 31, 2006,’’ as originally
required by French airworthiness
directive 2002–637(B), dated December
24, 2002. The commenter disagrees with
the compliance time of 48 months that
was specified in the original NPRM. The
commenter states that, although the
DGAC imposed a similar compliance
schedule when the French
airworthiness directive was issued 2
years ago (requiring compliance by
December 31, 2006), the modification
was developed several years ago and is
immediately available for
implementation on U.S. carriers. The
commenter sees no reason to prolong
the implementation simply because the
original NPRM was not issued at the
same time as the French airworthiness
directive.
We agree with the intent of the
commenter’s remarks. However, we
express compliance times based on
calendar dates (e.g., ‘‘not later than
December 31, 2006’’) only when
engineering analysis establishes a direct
relationship between the date and the
compliance time. In this case, no direct
relationship exists. The compliance
time, December 31, 2006, for the subject
modification specified in the French
airworthiness directive corresponds to
20 months after the effective date of the
original issue of French airworthiness
directive F–2005–057, dated April 13,
2005. Thus, the compliance time of 20
months after the effective date of this
AD for the modification is consistent
with the compliance time specified in
the French airworthiness directive. We
have changed the compliance time
specified in paragraph (g) of this
supplemental NPRM accordingly.
Explanation of Change to Applicability
We have revised the applicability of
the original NPRM to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
FAA’s Determination and Proposed
Requirements of the Supplemental
NPRM
The changes discussed above expand
the scope of the original NPRM;
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therefore, we have determined that it is
necessary to reopen the comment period
to provide additional opportunity for
public comment on this supplemental
NPRM.
Costs of Compliance
This proposed AD would affect about
517 airplanes of U.S. registry.
The modification that is required by
AD 2001–16–14 and retained in this
proposed AD takes about 7 work hours
per airplane, at an average labor rate of
$65 per work hour. The cost of required
parts is negligible. Based on these
figures, the estimated cost of the
currently required modification for U.S.
operators is $235,235, or $455 per
airplane.
The functional test that is required by
AD 2001–16–14 and retained in this
proposed AD takes about 1 work hour
per airplane, at an average labor rate of
$65 per work hour. Based on these
figures, the cost impact of the currently
required functional test for U.S.
operators is $33,605, or $65 per
airplane, per test cycle.
For airplanes that have not been
modified in accordance with AD 2001–
16–14: The new proposed modification
(including the new placard installation)
would take about 17 work hours per
airplane, at an average labor rate of $65
per work hour. Required parts would
cost about $5,130 per airplane. Based on
these figures, the estimated cost of the
new modification specified in this
proposed AD is $6,235 per airplane.
For airplanes that have been modified
in accordance with AD 2001–16–14:
The new proposed modification
(including the new placard installation)
would take about 21 work hours per
airplane, at an average labor rate of $65
per work hour. Required parts would
cost about $5,130 per airplane. Based on
these figures, the estimated cost of the
new modification specified in this
proposed AD is $6,495 per airplane.
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
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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 supplemental NPRM. 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 FAA amends § 39.13 by
removing amendment 39–12383 (66 FR
42939, August 16, 2001), and adding the
following new airworthiness directive
(AD):
Airbus: Docket No. FAA–2004–19863;
Directorate Identifier 2003–NM–29–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
August 15, 2005.
Affected ADs
(b) This AD supersedes AD 2001–16–14,
amendment 39–12383 (66 FR 42939, August
16, 2001).
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Applicability
(c) This AD applies to Airbus Model A319–
100, A320–200, and A321–100 and –200
series airplanes; certificated in any category;
equipped with telescopic girt bars of the
escape slide/raft assembly installed per
Airbus Modification 20234, or Airbus Service
Bulletin A320–25–1055 or A320–25–1218 in
service; except those airplanes with Airbus
Modification 31708.
Unsafe Condition
(d) This AD was prompted by development
of a new, improved modification of the
telescopic girt bar of the escape slide/raft
assembly. We are issuing this AD to prevent
failure of the escape slide/raft to deploy
correctly, which could result in the slide
being unusable during an emergency
evacuation and consequent injury to
passengers or airplane crewmembers.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2001–
16–14
Modification/Follow-On Actions
(f) For airplanes listed in Airbus Industrie
All Operators Telex A320–52A1111, Revision
01, dated July 23, 2001: Within 1,500 flight
hours after August 31, 2001 (the effective
date of AD 2001–16–14); except as provided
by paragraph (h) of this AD, modify the
telescopic girt bar of the escape slide/raft
assembly installed on all passenger and crew
doors and do a functional test to ensure the
girt bar does not retract, per Airbus Industrie
AOT A320–52A1111, Revision 01, dated July
23, 2001.
(1) If the girt bar retracts, before further
flight, replace any discrepant parts and do
another functional test to ensure the girt bar
does not retract, per the AOT. Repeat the
functional test thereafter at intervals not to
exceed 18 months until paragraph (g) of this
AD is accomplished.
(2) If the girt bar does not retract, repeat the
functional test thereafter at intervals not to
exceed 18 months.
Note 1: Modification and follow-on actions
accomplished prior to the effective date of
this AD per Airbus Industrie AOT A320–
52A1111, dated July 5, 2001, are considered
acceptable for compliance with the
applicable actions specified in this
amendment.
(2) Install a placard on each modified girt
bar.
(h) For airplanes on which the
modification of the telescopic girt bar
required by paragraph (g)(1) of this AD is
accomplished within the compliance time
specified in paragraph (f) of this AD,
accomplishing the modification required by
paragraph (f) is not required.
Modifications Accomplished According to
Previous Issues of Service Bulletin
(i) Modification of the telescopic girt bar
accomplished before the effective date of this
AD in accordance with Airbus Service
Bulletin A320–52–1112, dated January 16,
2002; Revision 01, dated April 3, 2002;
Revision 02, dated September 6, 2002;
Revision 03, dated June 27, 2003; or Revision
04, dated November 12, 2003; is considered
acceptable for compliance with the
modification of the telescopic girt bar
required by paragraph (g)(1) of this AD.
Parts Installation
(j) As of the effective date of this AD, no
person may install on any airplane a
telescopic girt bar of the escape slide/raft
assembly unless it has been modified as
required by paragraph (g) of this AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, International Branch,
Transport Airplane Directorate, ANM–116,
FAA, has the authority to approve alternative
methods of compliance (AMOCs) for this AD,
if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) AMOCs approved previously in
accordance with AD 2001–16–14,
amendment 39–12383, are approved as
AMOCs with paragraph (f) of this AD.
Related Information
(l) French airworthiness directives 2002–
637(B) R1, dated April 16, 2003, and F–2005–
057, dated April 13, 2005, also address the
subject of this AD.
Issued in Renton, Washington, on July 14,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–14394 Filed 7–20–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
New Requirements of This AD
Modification
(g) Within 20 months after the effective
date of this AD: Accomplish the actions
specified in paragraphs (g)(1) and (g)(2) of
this AD by doing all the applicable actions
specified in the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1112, Revision 05, dated June 25, 2004.
Accomplishing these actions terminates the
repetitive functional tests required by
paragraph (f) of this AD.
(1) Modify the telescopic girt bar of the
escape slide/raft assembly.
PO 00000
Frm 00006
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14 CFR Part 39
[Docket No. FAA–2005–21880; Directorate
Identifier 2004–NM–216–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767–300 and –300F Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
E:\FR\FM\21JYP1.SGM
21JYP1
]]>Agencies
[Federal Register Volume 70, Number 139 (Thursday, July 21, 2005)]
[Proposed Rules]
[Pages 42005-42008]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-14394]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19863; Directorate Identifier 2003-NM-29-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319-100, A320-200, and
A321-100 and -200 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 42006]]
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: The FAA is revising an earlier NPRM for an airworthiness
directive (AD) that applies to certain Airbus Model A319-100, A320-200,
and A321-100 and -200 series airplanes. The original NPRM would have
superseded an existing AD that currently requires modification of the
telescopic girt bar of the escape slide/raft assembly, and follow-on
actions. The original NPRM proposed to mandate a new modification of
the telescopic girt bar, which would terminate the repetitive
functional tests required by the existing AD. The original NPRM also
proposed to expand the applicability of the existing AD. The original
NPRM was prompted by development of a new, improved modification. This
new action would revise the original NPRM by proposing to mandate the
installation of placards on the modified girt bars, and reduce the
compliance time. We are proposing this supplemental NPRM to prevent
failure of the escape slide/raft to deploy correctly, which could
result in the slide being unusable during an emergency evacuation and
consequent injury to passengers or airplane crewmembers.
DATES: We must receive comments on this supplemental NPRM by August 15,
2005.
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.
For service information identified in this proposed AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2004-19863; the directorate identifier for this docket is
2003-NM-29-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 proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-19863;
Directorate Identifier 2003-NM-29-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this supplemental NPRM.
We will consider all comments received by the closing date and may
amend this supplemental NPRM in light of those comments.
We will post all comments submitted, 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 our
docket 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 can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
You can 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 ADDRESSES. Comments will be available in the
AD docket shortly after the Docket Management System (DMS) receives
them.
Discussion
We proposed to amend part 39 of the Federal Aviation Regulations
(14 CFR part 39) with a notice of proposed rulemaking (NPRM) for an AD
(the ``original NPRM'') for certain Airbus Model A319, A320, and A321
series airplanes. The original NPRM proposed to supersede AD 2001-16-
14, amendment 39-12383 (66 FR 42939, August 16, 2001), which applies to
certain Airbus Model A319, A320, and A321 series airplanes. The
original NPRM was published in the Federal Register on December 16,
2004 (69 FR 75273). The original NPRM proposed to retain the
requirements of the existing AD and mandate a new modification of the
telescopic girt bar, which would terminate the repetitive functional
tests of the existing AD. The original NPRM also proposed to expand the
applicability of the existing AD. The original NPRM was prompted by
development of a new, improved modification.
Comments
We have considered the following comments on the original NPRM.
Request To Add Revised Service Information
One commenter concurs with the content of the original NPRM and
asks that Airbus Service Bulletins A320-52-1112, Revision 03, dated
June 27, 2003; and Revision 04, dated November 12, 2003; be added as
additional sources of service information for accomplishing the new
modification. Revision 02 of the service bulletin was referenced in the
original NPRM as the appropriate source of service information for
accomplishing the modification of the telescopic girt bar of the escape
slide/raft assembly. The commenter notes that Revisions 03 and 04 of
the service bulletin did not change the content of Revision 02 of the
service bulletin, and should be allowed as an alternative method of
compliance.
Another commenter asks that Revision 05 of the referenced service
bulletin, dated June 25, 2004, be added to the original NPRM as the
source of service information for accomplishing the existing and new
requirements. The commenter notes that Revision 05 adds procedures for
the installation of a sticker (placard) on each of the four girt bars.
That installation was omitted in the procedures specified in previous
issues of the service bulletin. The commenter adds that the purpose of
the stickers is to provide positive visual indication of girt bar
engagement in the armed mode, and the Direction Generale de l'Aviation
Civile (DGAC), which is the airworthiness authority for France, is in
the process of issuing a new airworthiness directive to require
installation of those stickers.
We agree with the commenters. Airbus has issued, and we have
[[Page 42007]]
reviewed, Service Bulletins A320-52-1112, Revision 03, dated June 27,
2003; Revision 04, dated November 12, 2003; and Revision 05, dated June
25, 2004. No more work is necessary if Revisions 03 and 04 are used, as
they are essentially the same as Revision 02 of the service bulletin.
Revision 05 adds procedures for installing placards on the modified
telescopic girt bars of the escape slide/raft assembly.
The DGAC mandated compliance with Revision 05 of the service
bulletin and issued French airworthiness directive F-2005-057, dated
April 13, 2005, to ensure the continued airworthiness of these
airplanes in France.
We agree that the placards are needed to provide positive visual
indication of girt bar engagement in the armed mode. Therefore, we have
changed paragraph (g) of this supplemental NPRM to add paragraphs
(g)(1) and (g)(2), which specify modifying the telescopic girt bars and
installing placards on the modified girt bars using Revision 05 of the
service bulletin to accomplish those actions. In addition, we have
added Revisions 03 and 04 to paragraph (i) of this supplemental NPRM to
give credit for previous accomplishment of the modification of the
telescopic girt bar of the escape slide/raft assembly.
Request for Excluding Installation of Placards
One commenter asks that the installation of placards recommended in
Revision 05 of the referenced service bulletin be excluded from the
requirements of the original NPRM. The commenter states that Revision
05 added procedures for installing a ``dot'' placard to the modified
girt bar, for identification. The commenter notes that this placard
seems to be self-sticking with adhesive, and does not change the part
number of the modified girt bar. The commenter adds that the placard
will eventually come off and cause compliance issues in the future,
even though there are currently no such reports from Airbus. The
commenter also asks that references up to and including Revision 05 of
the service bulletin be added to the original NPRM as acceptable
sources for the instructions for the modification, with the exception
of the placard installation.
We do not agree with the commenter's request. We have determined
that installation of the placards, as identified in Revision 05 of the
service bulletin and required by French airworthiness directive F-2005-
057, is necessary and the placards should be maintained as part of
normal airplane maintenance. As stated previously, the purpose of the
stickers is to provide positive visual indication of girt bar
engagement in the armed mode. This visual indication will ensure
continued safe flight of the airplane. No change is made to the
supplemental NPRM in this regard.
Request To Reduce Compliance Time
The same commenter asks (as a follow-on to its previous request)
that we reduce the compliance time for the modification specified in
paragraph (g) of the original NPRM to ``not later than December 31,
2006,'' as originally required by French airworthiness directive 2002-
637(B), dated December 24, 2002. The commenter disagrees with the
compliance time of 48 months that was specified in the original NPRM.
The commenter states that, although the DGAC imposed a similar
compliance schedule when the French airworthiness directive was issued
2 years ago (requiring compliance by December 31, 2006), the
modification was developed several years ago and is immediately
available for implementation on U.S. carriers. The commenter sees no
reason to prolong the implementation simply because the original NPRM
was not issued at the same time as the French airworthiness directive.
We agree with the intent of the commenter's remarks. However, we
express compliance times based on calendar dates (e.g., ``not later
than December 31, 2006'') only when engineering analysis establishes a
direct relationship between the date and the compliance time. In this
case, no direct relationship exists. The compliance time, December 31,
2006, for the subject modification specified in the French
airworthiness directive corresponds to 20 months after the effective
date of the original issue of French airworthiness directive F-2005-
057, dated April 13, 2005. Thus, the compliance time of 20 months after
the effective date of this AD for the modification is consistent with
the compliance time specified in the French airworthiness directive. We
have changed the compliance time specified in paragraph (g) of this
supplemental NPRM accordingly.
Explanation of Change to Applicability
We have revised the applicability of the original NPRM to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
FAA's Determination and Proposed Requirements of the Supplemental NPRM
The changes discussed above expand the scope of the original NPRM;
therefore, we have determined that it is necessary to reopen the
comment period to provide additional opportunity for public comment on
this supplemental NPRM.
Costs of Compliance
This proposed AD would affect about 517 airplanes of U.S. registry.
The modification that is required by AD 2001-16-14 and retained in
this proposed AD takes about 7 work hours per airplane, at an average
labor rate of $65 per work hour. The cost of required parts is
negligible. Based on these figures, the estimated cost of the currently
required modification for U.S. operators is $235,235, or $455 per
airplane.
The functional test that is required by AD 2001-16-14 and retained
in this proposed AD takes about 1 work hour per airplane, at an average
labor rate of $65 per work hour. Based on these figures, the cost
impact of the currently required functional test for U.S. operators is
$33,605, or $65 per airplane, per test cycle.
For airplanes that have not been modified in accordance with AD
2001-16-14: The new proposed modification (including the new placard
installation) would take about 17 work hours per airplane, at an
average labor rate of $65 per work hour. Required parts would cost
about $5,130 per airplane. Based on these figures, the estimated cost
of the new modification specified in this proposed AD is $6,235 per
airplane.
For airplanes that have been modified in accordance with AD 2001-
16-14: The new proposed modification (including the new placard
installation) would take about 21 work hours per airplane, at an
average labor rate of $65 per work hour. Required parts would cost
about $5,130 per airplane. Based on these figures, the estimated cost
of the new modification specified in this proposed AD is $6,495 per
airplane.
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
[[Page 42008]]
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 supplemental NPRM. 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 FAA amends Sec. 39.13 by removing amendment 39-12383 (66 FR
42939, August 16, 2001), and adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2004-19863; Directorate Identifier 2003-NM-
29-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by August 15, 2005.
Affected ADs
(b) This AD supersedes AD 2001-16-14, amendment 39-12383 (66 FR
42939, August 16, 2001).
Applicability
(c) This AD applies to Airbus Model A319-100, A320-200, and
A321-100 and -200 series airplanes; certificated in any category;
equipped with telescopic girt bars of the escape slide/raft assembly
installed per Airbus Modification 20234, or Airbus Service Bulletin
A320-25-1055 or A320-25-1218 in service; except those airplanes with
Airbus Modification 31708.
Unsafe Condition
(d) This AD was prompted by development of a new, improved
modification of the telescopic girt bar of the escape slide/raft
assembly. We are issuing this AD to prevent failure of the escape
slide/raft to deploy correctly, which could result in the slide
being unusable during an emergency evacuation and consequent injury
to passengers or airplane crewmembers.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2001-16-14
Modification/Follow-On Actions
(f) For airplanes listed in Airbus Industrie All Operators Telex
A320-52A1111, Revision 01, dated July 23, 2001: Within 1,500 flight
hours after August 31, 2001 (the effective date of AD 2001-16-14);
except as provided by paragraph (h) of this AD, modify the
telescopic girt bar of the escape slide/raft assembly installed on
all passenger and crew doors and do a functional test to ensure the
girt bar does not retract, per Airbus Industrie AOT A320-52A1111,
Revision 01, dated July 23, 2001.
(1) If the girt bar retracts, before further flight, replace any
discrepant parts and do another functional test to ensure the girt
bar does not retract, per the AOT. Repeat the functional test
thereafter at intervals not to exceed 18 months until paragraph (g)
of this AD is accomplished.
(2) If the girt bar does not retract, repeat the functional test
thereafter at intervals not to exceed 18 months.
Note 1: Modification and follow-on actions accomplished prior to
the effective date of this AD per Airbus Industrie AOT A320-52A1111,
dated July 5, 2001, are considered acceptable for compliance with
the applicable actions specified in this amendment.
New Requirements of This AD
Modification
(g) Within 20 months after the effective date of this AD:
Accomplish the actions specified in paragraphs (g)(1) and (g)(2) of
this AD by doing all the applicable actions specified in the
Accomplishment Instructions of Airbus Service Bulletin A320-52-1112,
Revision 05, dated June 25, 2004. Accomplishing these actions
terminates the repetitive functional tests required by paragraph (f)
of this AD.
(1) Modify the telescopic girt bar of the escape slide/raft
assembly.
(2) Install a placard on each modified girt bar.
(h) For airplanes on which the modification of the telescopic
girt bar required by paragraph (g)(1) of this AD is accomplished
within the compliance time specified in paragraph (f) of this AD,
accomplishing the modification required by paragraph (f) is not
required.
Modifications Accomplished According to Previous Issues of Service
Bulletin
(i) Modification of the telescopic girt bar accomplished before
the effective date of this AD in accordance with Airbus Service
Bulletin A320-52-1112, dated January 16, 2002; Revision 01, dated
April 3, 2002; Revision 02, dated September 6, 2002; Revision 03,
dated June 27, 2003; or Revision 04, dated November 12, 2003; is
considered acceptable for compliance with the modification of the
telescopic girt bar required by paragraph (g)(1) of this AD.
Parts Installation
(j) As of the effective date of this AD, no person may install
on any airplane a telescopic girt bar of the escape slide/raft
assembly unless it has been modified as required by paragraph (g) of
this AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, International Branch, Transport Airplane
Directorate, ANM-116, FAA, has the authority to approve alternative
methods of compliance (AMOCs) for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) AMOCs approved previously in accordance with AD 2001-16-14,
amendment 39-12383, are approved as AMOCs with paragraph (f) of this
AD.
Related Information
(l) French airworthiness directives 2002-637(B) R1, dated April
16, 2003, and F-2005-057, dated April 13, 2005, also address the
subject of this AD.
Issued in Renton, Washington, on July 14, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-14394 Filed 7-20-05; 8:45 am]
BILLING CODE 4910-13-P
