Airworthiness Directives; Airbus Model A330, A340-200, and A340-300 Series Airplanes, 7386-7389 [05-2579]
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7386
Federal Register / Vol. 70, No. 29 / Monday, February 14, 2005 / Rules and Regulations
To prevent failure of both spring boxes of
certain VLAs due to corrosion damage, which
could result in loss of rudder control and
consequent reduced controllability of the
airplane, accomplish the following:
Restatement of the Requirements of AD
2001–22–02
(a) Within 10 days after November 13, 2001
(the effective date of AD 2001–22–02,
amendment 39–12481): Determine the part
and amendment numbers of the VLA of the
rudder control system to verify the parts were
installed using the correct standard, in
accordance with Airbus All Operators Telex
(AOT) A300–27A0196, dated September 20,
2001; or in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–27–0196, Revision 01,
dated November 13, 2002.
(1) If the part and amendment numbers
shown are not correct, as specified in the
AOT or the service bulletin, before further
flight, do a detailed inspection of the VLA tie
rod for damage (bent or ruptured rod) in
accordance with the AOT or the service
bulletin.
(i) If the tie rod is damaged, replace the
VLA with a new VLA in accordance with the
AOT or the service bulletin. Such
replacement ends the requirements of this
paragraph.
(ii) If the tie rod is not damaged, no further
action is required by this paragraph.
(2) If the part and amendment numbers
shown are correct, no further action is
required by this paragraph.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
New Requirements of This AD
(b) For airplanes having VLA spring boxes
with any part number (P/N) other than
418473–20 or 418473–200: Within 500 flight
hours after the effective date of this AD, do
a detailed inspection of the tie rod for
damage (bent or ruptured rod), by
accomplishing all of the applicable actions
specified in the Accomplishment
Instructions of Airbus Service Bulletin A300–
27–0196, Revision 01, dated November 13,
2002. Repeat the inspection thereafter at
intervals not to exceed 1,000 flight hours,
until paragraph (f) of this AD has been
accomplished.
Replacement or Repair
(c) If any damage is found to the VLA or
the rudder control system during any
inspection required by paragraph (a)(1) or (b)
of this AD, before further flight, replace the
VLA with a new VLA (including a follow-up
test) by accomplishing all of the applicable
actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A300–
27–0196, Revision 01, dated November 13,
2002.
No Reporting/Parts Return Requirements
(d) Although Airbus Service Bulletin
A300–27–0196, Revision 01, dated November
13, 2002, describes procedures for submitting
certain information to the manufacturer, and
for returning certain parts to the
manufacturer, this AD does not require those
actions.
Terminating Modification
(e) Within 24 months after the effective
date of this AD: Modify the applicable VLA,
as required by either paragraph (e)(1) or (e)(2)
of this AD, by accomplishing all of the
applicable actions specified in the
Accomplishment Instructions of Airbus
Service Bulletin A300–27–0198, dated
December 1, 2003. Accomplishing this
modification ends the repetitive inspections
required by paragraph (b) of this AD.
(1) For any VLA having a spring box with
P/N 418473–20 or 418473–200: Install a new
identification plate and re-identify the VLA.
(2) For any VLA having a spring box with
P/N 418473 or 418473–100: Modify the
spring box and re-identify the VLA.
Note 2: Airbus Service Bulletin A300–27–
0198, dated December 1, 2003, references
Goodrich Actuation Systems Service Bulletin
27–21–1H, Revision 3, dated December 8,
2003, as an additional source of service
information for accomplishing the
modification.
Alternative Methods of Compliance
(f) In accordance with 14 CFR 39.19, the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA, is
authorized to approve alternative methods of
compliance for this AD.
Incorporation by Reference
(g) Unless otherwise specified in this AD,
the actions must be done in accordance with
the service information in Table 1 of this AD.
Copies may be obtained from Airbus, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France. Copies may be inspected at
the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Airbus service information
Revision level
Date
All Operators Telex A300–27A0196 ................................................................................................................
Service Bulletin A300–27–0196, excluding Appendix 01 ...............................................................................
Service Bulletin A300–27–0198 ......................................................................................................................
Original ...............
01 ........................
Original ...............
Sept. 20, 2001.
Nov. 13, 2002.
Dec. 1, 2003.
(1) The incorporation by reference of
Airbus Service Bulletin A300–27–0196,
excluding Appendix 01, Revision 01, dated
November 13, 2002; and Airbus Service
Bulletin A300–27–0198, dated December 1,
2003; is approved by the Director of the
Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) The incorporation by reference of
Airbus All Operators Telex A300–27A0196,
dated September 20, 2001, was approved
previously by the Director of the Federal
Register as of November 13, 2001 (66 FR
54416, October 29, 2001).
Note 3: The subject of this AD is addressed
in French airworthiness directive F–2004–
091(B), dated June 23, 2004.
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Effective Date
DEPARTMENT OF TRANSPORTATION
(h) This amendment becomes effective on
March 21, 2005.
Federal Aviation Administration
Issued in Renton, Washington, on January
31, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–2581 Filed 2–11–05; 8:45 am]
14 CFR Part 39
BILLING CODE 4910–13–P
Airworthiness Directives; Airbus Model
A330, A340–200, and A340–300 Series
Airplanes
PO 00000
[Docket No. 2003–NM–256–AD; Amendment
39–13968; AD 2005–03–12]
RIN 2120–AA64
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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Federal Register / Vol. 70, No. 29 / Monday, February 14, 2005 / Rules and Regulations
SUMMARY: This amendment adopts a
new airworthiness directive (AD),
applicable to certain Airbus Model
A330, A340–200, and A340–300 series
airplanes. This AD requires initial and
repetitive inspections of certain frame
stiffeners to detect cracking. If any
cracking is found, this AD requires
replacement of the stiffener with a new,
reinforced stiffener. Replacement of the
stiffener constitutes terminating action
for certain inspections. This AD also
requires a one-time inspection of any
new, reinforced stiffener; and repair or
replacement of the new, reinforced
stiffener if any cracking is found during
the one-time inspection. This AD also
provides for an optional terminating
action for certain requirements of this
AD. The actions specified by this AD are
intended to prevent fatigue failure of
certain frame stiffener fittings, which
could result in reduced structural
integrity of the airplane. This action is
intended to address the identified
unsafe condition.
DATES: Effective March 21, 2005.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of March 21,
2005.
ADDRESSES: The service information
referenced in this AD may be obtained
from Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France.
This information may be examined at
the Federal Aviation Administration
(FAA), Transport Airplane Directorate,
Rules Docket, 1601 Lind Avenue, SW.,
Renton, Washington; or at the National
Archives and Records Administration
(NARA). For information on the
availability of this material at the
NARA, call (202) 741–6030, or go to
https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION: A
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an airworthiness directive (AD)
that is applicable to certain Airbus
Model A330, A340–200, and A340–300
series airplanes, was published as a
supplemental notice of proposed
rulemaking (NPRM) in the Federal
Register on November 22, 2004 (69 FR
67869). That supplemental NPRM
proposed to require initial and
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15:21 Feb 11, 2005
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repetitive inspections of certain frame
stiffeners to detect cracking. If any
cracking is found, that supplemental
NPRM proposed to require replacement
of the stiffener with a new, reinforced
stiffener. Replacement of the stiffener
would constitute terminating action for
certain inspections. That supplemental
NPRM also proposed to require a onetime inspection of any new, reinforced
stiffener; and repair or replacement of
the new, reinforced stiffener if any
cracking is found during the one-time
inspection. That supplemental NPRM
also provided for an optional
terminating action for certain
requirements of that supplemental
NPRM. In addition, that supplemental
NPRM also proposed to reduce the
compliance time for the initial
inspections of the affected frame
stiffeners.
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been submitted on the
supplemental NPRM or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed in the
supplemental NPRM.
Cost Impact
We estimate that 20 Model A330
airplanes of U.S. registry will be affected
by this AD, that it will take
approximately 4 work hours per
airplane to accomplish the required
inspection, and that the average labor
rate is $65 per work hour. Based on
these figures, the cost impact of the AD
on U.S. operators is estimated to be
$5,200, or $260 per airplane, per
inspection cycle.
The cost impact figure discussed
above is based on assumptions that no
operator has yet accomplished any of
the proposed requirements of this AD
action, and that no operator would
accomplish those actions in the future if
this AD were not adopted. The cost
impact figures discussed in AD
rulemaking actions represent only the
time necessary to perform the specific
actions actually required by the AD.
These figures typically do not include
incidental costs, such as the time
required to gain access and close up,
planning time, or time necessitated by
other administrative actions.
If an operator chooses to do the
optional terminating action rather than
continue the repetitive inspections, it
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7387
will take about 74 work hours per
airplane to accomplish the installations,
at an average labor rate of $65 per work
hour. Required parts will cost about
$7,860 per airplane. Based on these
figures, we estimate the cost of this
optional terminating action to be
$12,670 per airplane.
Currently, there are no affected Model
A340–200 or A340–300 series airplanes
on the U.S. Register. However, if an
affected airplane is imported and placed
on the U.S. Register in the future, it will
take approximately 4 work hours to
accomplish the required inspection, at
an average labor rate of $65 per work
hour. Based on these figures, we
estimate the cost of this AD to be $260
per airplane, per inspection cycle.
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 Impact
The regulations adopted herein will
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. Therefore, it is
determined that this final rule does not
have federalism implications under
Executive Order 13132.
For the reasons discussed above, I
certify that this action (1) is not a
‘‘significant regulatory action’’ under
Executive Order 12866; (2) is not a
‘‘significant rule’’ under 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. A final evaluation has
been prepared for this action and it is
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7388
Federal Register / Vol. 70, No. 29 / Monday, February 14, 2005 / Rules and Regulations
contained in the Rules Docket. A copy
of it may be obtained from the Rules
Docket at the location provided under
the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
inspection at intervals not to exceed 10,000
flight cycles until the replacement required
by paragraph (b) of this AD is accomplished;
or until the optional terminating action in
paragraph (d) of this AD is accomplished.
The actions in paragraphs (b) and (d) of this
AD constitute terminating action for the
repetitive inspections only for the side on
which the actions are taken.
Replacement
(b) If any cracking is detected during any
inspection required by paragraph (a) of this
AD: Before further flight, replace the affected
FR12A stiffener with a new reinforced
FR12A stiffener in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3135, Revision 01,
dated July 7, 2003; or Airbus Service Bulletin
A340–53–4141, Revision 02, dated August
13, 2004; as applicable. Replacement of the
stiffener constitutes terminating action for
the repetitive inspections required by
paragraph (a) of this AD, only for the side on
which the replacement is made.
2005–NM–03–12 Airbus: Amendment 39–
13968. Docket 2003–NM–256–AD.
Applicability: Model A330 series airplanes;
and Model A340–200 and A340–300 series
airplanes; certificated in any category; except
those on which Airbus Modification 49694
has been installed.
Compliance: Required as indicated, unless
accomplished previously.
To prevent fatigue failure of certain frame
stiffener fittings, which could result in
reduced structural integrity of the airplane,
accomplish the following:
Follow-On Inspection
(c) For airplanes on which a new,
reinforced stiffener is installed in accordance
with paragraph (b) of this AD: Within 14,600
flight cycles following the installation,
perform an HFEC inspection of the FR12A
stiffener fitting for cracking, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–53–3135,
Revision 01, dated July 7, 2003; or Airbus
Service Bulletin A340–53–4141, Revision 02,
dated August 13, 2004; as applicable. If any
cracking is detected, before further flight,
repair or replace the new reinforced stiffener
with a new stiffener in a manner approved
by either the Manager, International Branch,
´ ´
ANM–116, FAA; or the Direction Generale de
l’Aviation Civile (or its delegated agent).
Initial and Repetitive Inspections
(a) Prior to the accumulation of 13,000 total
flight cycles or within 6 months after the
effective date of this AD, whichever occurs
later: Conduct a high-frequency eddy current
(HFEC) inspection for cracking of the FR12A
stiffener fitting in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3135, Revision 01,
dated July 7, 2003 (for Model A330 series
airplanes); or Airbus Service Bulletin A340–
53–4141, Revision 02, dated August 13, 2004
(for Model A340–200 and A340–300 series
airplanes); as applicable. Repeat the
Optional Terminating Action
(d) Replacement of the FR12A stiffeners
with new, reinforced stiffeners; installation
of new reinforced junction fittings between
FR12A/FR13 and FR13/FR13A at the stringer
26 level; and installation of a new shear web
that joins the fitting to the cabin floor track;
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
53–3130, Revision 01, dated October 10,
2003; or Airbus Service Bulletin A340–53–
4137, Revision 01, dated October 10, 2003; as
applicable; constitutes terminating action for
the inspection requirements of paragraphs (a)
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
the following new airworthiness
directive:
I
and (c) of this AD, only for the side on which
the replacement and installations are made.
Actions Accomplished per Previous Issues of
Service Bulletins
(e) Actions accomplished before the
effective date of this AD in accordance with
the Accomplishment Instructions of Airbus
Service Bulletins A330–53–3130, dated May
26, 2003; A330–53–3135, dated May 26,
2003; A340–53–4137, dated May 26, 2003;
A340–53–4141, dated May 26, 2003; or
A340–53–4141, Revision 01, dated July 7,
2003; are considered acceptable for
compliance only with the following
requirements of this AD: The HFEC
inspections required by paragraph (a) of this
AD, the replacement required by paragraph
(b) of this AD, and the actions in paragraph
(d) of this AD.
No Reporting Requirements
(f) Although the Accomplishment
Instructions of Airbus Service Bulletin A330–
53–3135, Revision 01, dated July 7, 2003; and
Airbus Service Bulletin A340–53–4141,
Revision 02, dated August 13, 2004; describe
procedures for submitting certain
information to the manufacturer, this AD
does not require those actions.
Alternative Methods of Compliance
(g) In accordance with 14 CFR 39.19, the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA, is
authorized to approve alternative methods of
compliance for this AD.
Incorporation by Reference
(h) Unless otherwise specified in this AD,
the actions must be done in accordance with
the service information listed in Table 1 of
this AD, as applicable. This incorporation by
reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Copies may be
obtained from Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France.
Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Revision
level
Airbus Service Bulletin
A330–53–3130
A330–53–3135
A340–53–4137
A340–53–4141
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........................................................................................................................................................
........................................................................................................................................................
........................................................................................................................................................
15:21 Feb 11, 2005
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PO 00000
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14FER1
01
01
01
02
Date
October 10, 2003.
July 7, 2003.
October 10, 2003.
August 13, 2004.
Federal Register / Vol. 70, No. 29 / Monday, February 14, 2005 / Rules and Regulations
Note 1: The subject of this AD is addressed
in French airworthiness directives 2003–
205(B), dated May 28, 2003; and 2003–
206(B), dated May 28, 2003.
Effective Date
(i) This amendment becomes effective on
March 21, 2005.
Issued in Renton, Washington, on January
31, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–2579 Filed 2–11–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19561; Directorate
Identifier 2004–NM–50–AD; Amendment 39–
13972; AD 2005–03–16]
RIN 2120–AA64
Airworthiness Directives; Raytheon
Model DH.125, HS.125, and BH.125
Series Airplanes; BAe.125 Series 800A
(C–29A and U–125) and 800B
Airplanes; and Hawker 800 (Including
Variant U–125A) and 800XP Airplanes;
Equipped with TFE731 Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Raytheon Model DH.125, HS.125, and
BH.125 series airplanes; BAe.125 series
800A (C–29A and U–125) and 800B
airplanes; and Hawker 800 (including
variant U–125A) and 800XP airplanes.
This AD requires installing insulating
blankets on the engine compartment
firewall and the wire harness passing
through the firewall fairlead. This AD is
prompted by a report indicating that
insulation on the wire harness passing
through the firewall fairlead ignited on
the fuselage side of the firewall. We are
issuing this AD to prevent a fire in the
engine compartment from causing
possible ignition of outgassing wire
insulation on the fuselage side of the
firewall, which could lead to an
uncontrollable fire in the fuselage.
DATES: This AD becomes effective
March 21, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of March 21, 2005.
ADDRESSES: For service information
identified in this AD, contact Raytheon
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15:21 Feb 11, 2005
Jkt 205001
Aircraft Company, Department 62, P.O.
Box 85, Wichita, Kansas 67201–0085.
You can examine this information at the
National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030,
or go to: https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. 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 U.S. Department of Transportation,
400 Seventh Street, SW., room PL–401,
Washington, DC. This docket number is
FAA–2004–19561; the directorate
identifier for this docket is 2004–NM–
50–AD.
FOR FURTHER INFORMATION CONTACT: Jeff
Pretz, Aerospace Engineer, Airframe
Branch, ACE–118W, FAA, Wichita
Aircraft Certification Office, 1801
Airport Road, room 100, Mid-Continent
Airport, Wichita, Kansas 67209;
telephone (316) 946–4153; fax (316)
946–4407.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR Part 39 with
an AD for certain Raytheon Model
DH.125, HS.125, and BH.125 series
airplanes; BAe.125 series 800A (C–29A
and U–125) and 800B airplanes; and
Hawker 800 (including variant U–125A)
and 800XP airplanes. That action,
published in the Federal Register on
November 10, 2004 (69 FR 65103),
proposed to require installing insulating
blankets on the engine compartment
firewall and the wire harness passing
through the firewall fairlead.
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been submitted on the proposed
AD or on the determination of the cost
to the public.
Explanation of Change Made to the
Proposal
We inadvertently left the paragraph
number off the paragraph headed ‘‘No
Reporting Requirement’’ between
paragraphs (f) and (g) of the proposed
AD. We have identified the specified
paragraph as (g) and reidentified the
original paragraph (g) to (h) in the final
rule.
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7389
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the change
described previously. We have
determined that this change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
There are about 804 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 530 airplanes
of U.S. registry. The actions will take
about 8 work hours per airplane, at an
average labor rate of $65 per work hour.
Required parts will cost about $1,784
per airplane. Based on these figures, the
estimated cost of the AD for U.S.
operators is $1,221,120, or $2,304 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
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 AD will
not have federalism implications under
Executive Order 13132. This AD will
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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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
E:\FR\FM\14FER1.SGM
14FER1
]]>Agencies
[Federal Register Volume 70, Number 29 (Monday, February 14, 2005)]
[Rules and Regulations]
[Pages 7386-7389]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2579]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-256-AD; Amendment 39-13968; AD 2005-03-12]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330, A340-200, and A340-
300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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[[Page 7387]]
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A330, A340-200, and A340-300 series
airplanes. This AD requires initial and repetitive inspections of
certain frame stiffeners to detect cracking. If any cracking is found,
this AD requires replacement of the stiffener with a new, reinforced
stiffener. Replacement of the stiffener constitutes terminating action
for certain inspections. This AD also requires a one-time inspection of
any new, reinforced stiffener; and repair or replacement of the new,
reinforced stiffener if any cracking is found during the one-time
inspection. This AD also provides for an optional terminating action
for certain requirements of this AD. The actions specified by this AD
are intended to prevent fatigue failure of certain frame stiffener
fittings, which could result in reduced structural integrity of the
airplane. This action is intended to address the identified unsafe
condition.
DATES: Effective March 21, 2005.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 21, 2005.
ADDRESSES: The service information referenced in this AD may be
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France. This information may be examined at the Federal Aviation
Administration (FAA), Transport Airplane Directorate, Rules Docket,
1601 Lind Avenue, SW., Renton, Washington; or at the National Archives
and Records Administration (NARA). For information on the availability
of this material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/ibr_
locations.html.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Airbus Model A330, A340-
200, and A340-300 series airplanes, was published as a supplemental
notice of proposed rulemaking (NPRM) in the Federal Register on
November 22, 2004 (69 FR 67869). That supplemental NPRM proposed to
require initial and repetitive inspections of certain frame stiffeners
to detect cracking. If any cracking is found, that supplemental NPRM
proposed to require replacement of the stiffener with a new, reinforced
stiffener. Replacement of the stiffener would constitute terminating
action for certain inspections. That supplemental NPRM also proposed to
require a one-time inspection of any new, reinforced stiffener; and
repair or replacement of the new, reinforced stiffener if any cracking
is found during the one-time inspection. That supplemental NPRM also
provided for an optional terminating action for certain requirements of
that supplemental NPRM. In addition, that supplemental NPRM also
proposed to reduce the compliance time for the initial inspections of
the affected frame stiffeners.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been submitted on the
supplemental NPRM or on the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
in the supplemental NPRM.
Cost Impact
We estimate that 20 Model A330 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 4 work hours per
airplane to accomplish the required inspection, and that the average
labor rate is $65 per work hour. Based on these figures, the cost
impact of the AD on U.S. operators is estimated to be $5,200, or $260
per airplane, per inspection cycle.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this AD were not adopted. The cost impact figures
discussed in AD rulemaking actions represent only the time necessary to
perform the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
If an operator chooses to do the optional terminating action rather
than continue the repetitive inspections, it will take about 74 work
hours per airplane to accomplish the installations, at an average labor
rate of $65 per work hour. Required parts will cost about $7,860 per
airplane. Based on these figures, we estimate the cost of this optional
terminating action to be $12,670 per airplane.
Currently, there are no affected Model A340-200 or A340-300 series
airplanes on the U.S. Register. However, if an affected airplane is
imported and placed on the U.S. Register in the future, it will take
approximately 4 work hours to accomplish the required inspection, at an
average labor rate of $65 per work hour. Based on these figures, we
estimate the cost of this AD to be $260 per airplane, per inspection
cycle.
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 Impact
The regulations adopted herein will 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action
and it is
[[Page 7388]]
contained in the Rules Docket. A copy of it may be obtained from the
Rules Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2005-NM-03-12 Airbus: Amendment 39-13968. Docket 2003-NM-256-AD.
Applicability: Model A330 series airplanes; and Model A340-200
and A340-300 series airplanes; certificated in any category; except
those on which Airbus Modification 49694 has been installed.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue failure of certain frame stiffener fittings,
which could result in reduced structural integrity of the airplane,
accomplish the following:
Initial and Repetitive Inspections
(a) Prior to the accumulation of 13,000 total flight cycles or
within 6 months after the effective date of this AD, whichever
occurs later: Conduct a high-frequency eddy current (HFEC)
inspection for cracking of the FR12A stiffener fitting in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A330-53-3135, Revision 01, dated July 7, 2003 (for Model A330 series
airplanes); or Airbus Service Bulletin A340-53-4141, Revision 02,
dated August 13, 2004 (for Model A340-200 and A340-300 series
airplanes); as applicable. Repeat the inspection at intervals not to
exceed 10,000 flight cycles until the replacement required by
paragraph (b) of this AD is accomplished; or until the optional
terminating action in paragraph (d) of this AD is accomplished. The
actions in paragraphs (b) and (d) of this AD constitute terminating
action for the repetitive inspections only for the side on which the
actions are taken.
Replacement
(b) If any cracking is detected during any inspection required
by paragraph (a) of this AD: Before further flight, replace the
affected FR12A stiffener with a new reinforced FR12A stiffener in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-53-3135, Revision 01, dated July 7, 2003; or Airbus
Service Bulletin A340-53-4141, Revision 02, dated August 13, 2004;
as applicable. Replacement of the stiffener constitutes terminating
action for the repetitive inspections required by paragraph (a) of
this AD, only for the side on which the replacement is made.
Follow-On Inspection
(c) For airplanes on which a new, reinforced stiffener is
installed in accordance with paragraph (b) of this AD: Within 14,600
flight cycles following the installation, perform an HFEC inspection
of the FR12A stiffener fitting for cracking, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3135,
Revision 01, dated July 7, 2003; or Airbus Service Bulletin A340-53-
4141, Revision 02, dated August 13, 2004; as applicable. If any
cracking is detected, before further flight, repair or replace the
new reinforced stiffener with a new stiffener in a manner approved
by either the Manager, International Branch, ANM-116, FAA; or the
Direction Generale de l'Aviation Civile (or its delegated agent).
Optional Terminating Action
(d) Replacement of the FR12A stiffeners with new, reinforced
stiffeners; installation of new reinforced junction fittings between
FR12A/FR13 and FR13/FR13A at the stringer 26 level; and installation
of a new shear web that joins the fitting to the cabin floor track;
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-53-3130, Revision 01, dated October 10, 2003; or
Airbus Service Bulletin A340-53-4137, Revision 01, dated October 10,
2003; as applicable; constitutes terminating action for the
inspection requirements of paragraphs (a) and (c) of this AD, only
for the side on which the replacement and installations are made.
Actions Accomplished per Previous Issues of Service Bulletins
(e) Actions accomplished before the effective date of this AD in
accordance with the Accomplishment Instructions of Airbus Service
Bulletins A330-53-3130, dated May 26, 2003; A330-53-3135, dated May
26, 2003; A340-53-4137, dated May 26, 2003; A340-53-4141, dated May
26, 2003; or A340-53-4141, Revision 01, dated July 7, 2003; are
considered acceptable for compliance only with the following
requirements of this AD: The HFEC inspections required by paragraph
(a) of this AD, the replacement required by paragraph (b) of this
AD, and the actions in paragraph (d) of this AD.
No Reporting Requirements
(f) Although the Accomplishment Instructions of Airbus Service
Bulletin A330-53-3135, Revision 01, dated July 7, 2003; and Airbus
Service Bulletin A340-53-4141, Revision 02, dated August 13, 2004;
describe procedures for submitting certain information to the
manufacturer, this AD does not require those actions.
Alternative Methods of Compliance
(g) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, is authorized
to approve alternative methods of compliance for this AD.
Incorporation by Reference
(h) Unless otherwise specified in this AD, the actions must be
done in accordance with the service information listed in Table 1 of
this AD, as applicable. This incorporation by reference was approved
by the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Copies may be obtained from Airbus, 1 Rond
Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
Table 1.--Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Airbus Service Bulletin level Date
------------------------------------------------------------------------
A330-53-3130.................... 01 October 10, 2003.
A330-53-3135.................... 01 July 7, 2003.
A340-53-4137.................... 01 October 10, 2003.
A340-53-4141.................... 02 August 13, 2004.
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[[Page 7389]]
Note 1: The subject of this AD is addressed in French
airworthiness directives 2003-205(B), dated May 28, 2003; and 2003-
206(B), dated May 28, 2003.
Effective Date
(i) This amendment becomes effective on March 21, 2005.
Issued in Renton, Washington, on January 31, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-2579 Filed 2-11-05; 8:45 am]
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