[Federal Register Volume 70, Number 223 (Monday, November 21, 2005)]
[Proposed Rules]
[Pages 70048-70052]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-22971]
========================================================================
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. 70, No. 223 / Monday, November 21, 2005 /
Proposed Rules
[[Page 70048]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23007; Directorate Identifier 2005-NM-013-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-200 and -300 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus Model A310-200 and -300 series airplanes. This
proposed AD would require repetitive inspections for cracks and
corrosion of the areas behind the scuff plates below the passenger/crew
doors and bulk cargo door, and repair of any cracked or corroded part.
This proposed AD also would require repetitive inspections for cracks
of the holes of the corner doublers, the fail-safe ring, and the door
frames of the passenger/crew door structures. This proposed AD is
prompted by reports of corrosion behind the scuff plates at passenger/
crew doors and the bulk cargo door and fatigue cracks on the corner
doublers of the forward and aft passenger/crew door frames. We are
proposing this AD to prevent such corrosion and fatigue cracking, which
could result in reduced structural integrity of the door surroundings.
DATES: We must receive comments on this proposed AD by December 21,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://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.
By 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
http://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-2005-23007; the directorate identifier for this docket is
2005-NM-013-AD.
FOR FURTHER INFORMATION CONTACT: Rosanne Ryburn, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2139; 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 under ADDRESSES. Include ``Docket No. FAA-2005-23007;
Directorate Identifier 2005-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 submitted 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 http://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 http://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at http://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 DMS receives them.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on certain Airbus Model A310-200 and -300
series airplanes. The DGAC advises that it received reports indicating
that corrosion was found behind the scuff plates at passenger/crew
doors and the bulk cargo door. The DGAC also advises that results of
structural fatigue testing have revealed that cracks were found on the
corner doublers of the forward and aft passenger/crew door frames; and,
after various simulated flights, on the fail-safe ring and frames 14
and 16A of the forward passenger/crew door. After 50,000 simulated
flights, cracks measuring between 8.0 millimeters (mm) and 109.0 mm
were found on the forward door frames and fail-safe ring. After 60,493
simulated flights, a 53.0 mm crack was found on the mid door frame.
After 106,000 simulated flights, a 32.0 mm crack was found on the aft
door frame. In all cases, the cracks originated at the fastener holes.
In addition, cracks originating from corner doubler edges were found at
the aft passenger/crew doors.
Such corrosion and fatigue cracking, if not detected and corrected,
could result in reduced structural integrity of the door surroundings.
[[Page 70049]]
Other Relevant Rulemaking
We have previously issued AD 97-11-03, amendment 39-10032 (62 FR
28325, May 23, 1997), applicable to all Airbus Model A300 series
airplanes. That AD requires inspections of the lower door surrounding
structure to detect cracks and corrosion; inspections to detect
cracking of the holes of the corner doublers, the fail-safe ring, and
the door frames of the door structures; and repair if necessary. That
AD also requires modification of the passenger/crew door frames, which
terminates certain inspections.
We also previously issued AD 98-16-05, amendment 39-10680 (63 FR
40812, July 31, 1998), applicable to all Airbus Model A300-600 series
airplanes. That AD requires inspections of the areas behind the scuff
plates below the passenger/crew doors and bulk cargo door to detect
cracks and corrosion; inspections to detect cracking of the holes of
the corner doublers, the fail-safe ring, and the door frames of the
door structures; and repair if necessary. In addition, that AD provides
for an optional terminating action for certain inspections. We are
considering further rulemaking to mandate the optional terminating
action.
Relevant Service Information
Airbus has issued the service bulletins in the following table:
Service Bulletins
------------------------------------------------------------------------
Airbus Service Bulletin-- Describes procedures for--
------------------------------------------------------------------------
A310-53-2030, Revision 06, dated July Doing initial inspections for
2, 1996. cracks and corrosion of the
areas behind the scuff plates
below the passenger/crew doors
and bulk cargo door, and
repairing any cracked or
corroded part.
A310-53-2041, Revision 02, dated July Doing repetitive inspections
2, 1996. for cracks and corrosion of
the areas behind the scuff
plates below the passenger/
crew doors and bulk cargo
door, and repairing any
cracked or corroded part.
A310-53-2037, Revision 02, dated Doing repetitive inspections
November 27, 2000. for cracks of the holes of the
corner doublers, the fail-safe
ring, and the door frames of
the passenger/crew door
structures, and repairing any
cracked part.
A310-53-2017, Revision 09, dated May Modifying the passenger/crew
17, 2004. door structures, which ends
the repetitive inspections of
the holes of the corner
doublers, fail-safe ring, and
the door frames for certain
airplanes. The modification
includes cold expansion of
fastener holes; a ROTO test;
installation of new oversize
fasteners and modified
brackets; and installation of
an additional steel doubler.
------------------------------------------------------------------------
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 directives
1991-132-124(B) R1, issued November 29, 2000, and F-2004-103, issued
July 7, 2004, to ensure the continued airworthiness of these airplanes
in France.
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 we need to
issue an AD for products of this type design that are certificated for
operation in the United States. Therefore, we are proposing this AD,
which would require accomplishing the applicable actions specified in
the service information described previously, except as discussed under
``Differences Between the Proposed AD, French Airworthiness Directive,
and Service Bulletins.''
Differences Between the Proposed AD, French Airworthiness Directive,
and Service Bulletins
Airbus Service Bulletin A310-53-2030 also does not list a grace
period for certain compliance times. This proposed AD adds a grace
period to certain compliance times. We find that a grace period will
keep airplanes from being grounded unnecessarily.
Airbus Service Bulletins A310-53-2041 and A310-53-2037 specify
repetitive inspections at ``every'' specified interval; however, this
proposed AD would require compliance ``at intervals not to exceed'' the
time specified in the service bulletin. These service bulletins also
specify compliance times in ``flights.'' This proposed AD would specify
those times as flight cycles. In addition, Airbus Service Bulletin
A310-53-2037 does not specify a starting date for the threshold for the
initial inspections. This proposed AD would require compliance before
the specified compliance time after the effective date of this AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD. The average labor rate per hour is
$65.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Parts Cost per registered Fleet cost
airplane airplanes
----------------------------------------------------------------------------------------------------------------
Initial inspections behind 26............. None........... $1,690......... 46 $77,740.
scuff plates (for all
airplanes).
Repetitive inspections 26............. None........... $1,690......... 46 $77,740, per
behind scuff plates, per inspection
inspection cycle (for all cycle.
airplanes).
[[Page 70050]]
Inspections of corner Between 4 and None........... Between $260 46 Between
doublers, fail-safe ring, 50 depending and $3,250. $11,960, and
and door frames, per on kit $149,500 per
inspection cycle. purchased. inspection
cycle.
Terminating modification for Between 8 and Between $506 Between $1,026 46 Between $47,196
repetitive inspection of 55 depending and $6,098 and $9,673. and $444,958.
corner doublers, fail-safe on kit depending on
ring, and door frames. purchased. kit purchased.
----------------------------------------------------------------------------------------------------------------
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 0130132. 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. 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), 401013, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2005-23007; Directorate Identifier 2005-NM-
013-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by December
21, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A310-203, -204, -221, and -
222 airplanes; and Airbus Model A310-304, -322, -324, and -325
airplanes; certificated in any category; excluding those airplanes
on which Airbus Modification 5068, 7201, and 7298 have been
incorporated in production.
Unsafe Condition
(d) This AD was prompted by reports of corrosion behind the
scuff plates at passenger/crew doors and the bulk cargo door and
fatigue cracks on the corner doublers of the forward and aft
passenger/crew door frames. We are issuing this AD to prevent such
corrosion and fatigue cracking, which could result in reduced
structural integrity of the door surroundings.
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.
Initial Inspections Behind Scuff Plates
(f) Do initial inspections (i.e., non-destructive tests) for
cracks and corrosion of the areas behind the scuff plates below the
passenger/crew doors and bulk cargo door, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-53-2030,
Revision 06, dated July 2, 1996. Do the inspections at the
applicable time specified in paragraphs (f)(1) and (f)(2) of Table 1
of this AD. If a records check cannot positively identify if the
applicable modification or service information specified in
paragraphs (f)(1) and (f)(2) of this AD has been done, assume that
it has not.
Table 1.--Compliance Time Requirements for Initial Inspections Behind
Scuff Plates
------------------------------------------------------------------------
For airplanes on which
Modification 5382S6526 for
the forward doors and And-- Inspect--
Modification 5382D4741 for
all other doors--
------------------------------------------------------------------------
(1) Have been incorporated None................ Within 108 months
in production. after first flight.
(2) Have not been (i) Airbus Service Within 48 months
incorporated in production. Information Letter since the date of
(SIL) A300-53-033, issuance of the
Revision 2, dated original standard
November 23, 1984, Airworthiness
for all doors, was Certificate or the
not followed; or date of issuance of
Airbus Service the original Export
Bulletin A310-53- Certificate of
2004, Revision 2, Airworthiness, or
March 9, 1984 (only within 12 months
applicable for the after the effective
forward doors), was date of this AD,
not done. whichever occurs
later.
[[Page 70051]]
(ii) Airbus SIL A300- Within 60 months
53-033, Revision 2, since the date of
dated November 23, issuance of the
1984, for all original
doors, was Airworthiness
followed; or Airbus Certificate or the
Service Bulletin date of issuance of
A310-53-2004, the original Export
Revision 2, dated Certificate of
March 9, 1984 (only Airworthiness, or
applicable for the within 12 months
forward doors), was after the effective
done. date of this AD,
whichever occurs
later.
(iii) Airbus SIL Within 12 months
A300-53-033, after the effective
Revision 2, dated date of this AD.
November 23, 1984,
for all doors, was
followed; or Airbus
Service Bulletin
A310-53-2004,
Revision 2, dated
March 9, 1984 (only
applicable for the
forward doors), was
done more than 48
months ago as of
the effective date
of this AD.
------------------------------------------------------------------------
Repetitive Inspections Behind Scuff Plates
(g) Following the initial inspection required by paragraph (f)
of this AD, do repetitive inspections (i.e., non-destructive tests)
for cracks and corrosion of the areas behind the scuff plates below
the passenger/crew doors and bulk cargo door, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-53-2041,
Revision 02, dated July 2, 1996. Repeat the inspections at the
applicable times specified in paragraphs (g)(1) through (g)(4) of
Table 2 of this AD.
Table 2.--Compliance Time Requirements for Repetitive Inspections Behind Scuff Plates
----------------------------------------------------------------------------------------------------------------
Unless in case of
corrosion removal,
For-- At-- Inspect at intervals then inspect at
not to exceed-- intervals not to
exceed--
----------------------------------------------------------------------------------------------------------------
(1) All airplanes.................. The forward passenger/crew 60 months............. None.
doors and the bulk cargo
door.
(2) All airplanes.................. The aft passenger/crew 60 months............. None.
doors, except the upper
and lower edges of the
door frame panel cutout.
(3) Model A310-203, -204, -221, and The aft passenger/crew 60 months or 12,000 60 months or 9,600
-222 airplanes. doors, the upper and lower flight cycles, flight cycles,
edges of the door frame whichever occurs whichever occurs
panel cutout. first. first.
(4) Model A310-304, -322, -324, and The aft passenger/crew 60 months or 7,000 60 months or 5,600
-325 airplanes. doors, the upper and lower flight cycles, flight cycles,
edges of the door frame whichever occurs whichever occurs
panel cutout. first. first.
----------------------------------------------------------------------------------------------------------------
Repetitive Inspections of Corner Doublers, Fail-Safe Ring, and Door
Frames
(h) Do inspections (i.e., rotating probe, x-ray, and general
visual, as applicable) for cracks of the holes of the corner
doublers, the fail-safe ring, and the door frames of the passenger/
crew door structures, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310-53-2037, Revision 02,
dated November 27, 2000. Do the inspections at the applicable times
specified in paragraphs (h)(1) through (h)(3) of Table 3 of this AD,
until the modification required by paragraph (k) of this AD is done.
Table 3.--Compliance Time Requirements for Repetitive Inspections of
Corner Doublers, Fail-Safe Ring, and Door Frames
------------------------------------------------------------------------
For-- Inspect-- And--
------------------------------------------------------------------------
(1) The upper corners of the Before the Do rotating probe
forward doors. accumulation of inspections at
20,000 total flight intervals not to
cycles, or within exceed 6,000 flight
2,000 flight cycles cycles.
after the effective
date of this AD,
whichever occurs
later.
(2) The lower corners of the Before the Do rotating probe
forward doors. accumulation of inspections at
20,000 total flight intervals not to
cycles, or within exceed 10,000
4,000 flight cycles flight cycles.
after the effective
date of this AD,
whichever occurs
later.
(3) The upper and lower Before the Do rotating probe
corners and parts accumulation of inspections at
underneath the corners of 20,000 total flight intervals not to
the upper door frames of cycles, or within exceed 8,000 flight
the aft doors. 4,000 flight cycles cycles or do x-ray
after the effective inspections at
date of this AD, intervals not to
whichever occurs exceed 3,500 flight
later. cycles; and do
general visual
inspections of
areas around
fasteners in
vicinity of
stringer 12 of the
upper door frames
at intervals not to
exceed 6,900 flight
cycles.
------------------------------------------------------------------------
[[Page 70052]]
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
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all 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.''
Corrective Actions
(i) If any crack or corrosion is found during any inspection
required by this AD, before further flight, do the applicable
corrective action in paragraph (i)(1) through (i)(3) of Table 4 of
this AD, except as provided by paragraph (j) of this AD.
Table 4.--Corrective Actions
------------------------------------------------------------------------
In accordance with
If-- Then-- the accomplishment
instructions of--
------------------------------------------------------------------------
(1) Any crack or corrosion Repair the cracked Airbus Service
is found during any or corroded part. Bulletin A310-53-
inspection required by 2030, Revision 06,
paragraph (f) of this AD. dated July 2, 1996.
(2) Any crack or corrosion Repair the cracked Airbus Service
is found during any or corroded part. Bulletin A310-53-
repetitive inspection 2041, Revision 02,
required by paragraph (g) dated July 2, 1996.
of this AD.
(3) Any crack is found Repair the cracked Airbus Service
during any inspection part. Bulletin A310-53-
required by paragraph (h) 2037, Revision 02,
of this AD. dated November 27,
2000.
------------------------------------------------------------------------
(j) If any crack or corrosion is found during any inspection
required by this AD, and the service bulletin recommends contacting
Airbus for appropriate action: Before further flight, repair the
cracked or corroded part in accordance with a method approved by
either the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate; or the Direction G[eacute]n[eacute]rale de
l'Aviation Civile (DGAC) (or its delegated agent).
Terminating Modification for Repetitive Inspection of Corner Doublers,
Fail-Safe Ring, and Door Frames
(k) Modify the passenger/crew door structures in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A310-53-
2017, Revision 09, dated May 17, 2004. Do the modification at the
applicable time in paragraph (k)(1) or (k)(2) of Table 5 of this AD.
Accomplishment of this modification constitutes terminating action
for the repetitive inspections required by paragraph (h) of this AD.
The inspections required by paragraph (f) of this AD must be done
before accomplishing this modification.
Table 5.--Compliance Time for Terminating Modification
------------------------------------------------------------------------
For model-- Compliance time
------------------------------------------------------------------------
(1) A310-203, -204, -221, and -222 Before the accumulation of
airplanes. 40,000 flight cycles since the
date of issuance of the
original standard
Airworthiness Certificate or
the date of issuance of the
original Export Certificate of
Airworthiness, or during the
next inspection required by
paragraph (h) of this AD,
whichever occurs later.
(2) A310-304, -322, -324, and -325 Before the accumulation of
airplanes. 35,000 flight cycles since the
date of issuance of the
original standard
Airworthiness Certificate or
the date of issuance of the
original Export Certificate of
Airworthiness, or during the
next inspection required by
paragraph (h) of this AD,
whichever occurs later.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 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
(m) French airworthiness directives 1991-132-124(B) R1, issued
November 29, 2000, and F-2004-103, issued July 7, 2004, also address
the subject of this AD.
Issued in Renton, Washington, on November 9, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-22971 Filed 11-18-05; 8:45 am]
BILLING CODE 4910-13-P