Airworthiness Directives; Airbus Model A310 Series Airplanes, 8728-8732 [E9-3765]
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Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations
(1) Within 15 months after the effective
date of this AD: Install the AIMS Blockpoint
2006 (BP06) operational software by doing all
the actions in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 777–31A0119 or 777–
31A0120, both Revision 2, both dated June
12, 2008; as applicable.
(2) Prior to or concurrently with
accomplishing the software installation,
install the AIMS Blockpoint 2005A (BP05A)
software in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–31–
0098, Revision 1, dated May 3, 2007; or
Boeing Special Attention Service Bulletin
777–31–0097, Revision 3, dated February 22,
2007; as applicable.
Credit for Actions Done Using Previous
Service Information
(g) Actions accomplished before the
effective date of this AD in accordance with
Boeing Service Bulletin 777–31–0119, dated
October 16, 2006, or Boeing Alert Service
Bulletin 777–31A0119, Revision 1, dated
March 27, 2007; and Boeing Service Bulletin
777–31–0120, dated October 16, 2006, or
Boeing Alert Service Bulletin 777–31A0120,
Revision 1, dated March 23, 2007; are
considered acceptable for compliance with
the corresponding actions specified in this
AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN: Jay
Yi, Aerospace Engineer, Systems and
Equipment Branch, ANM–130S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone (425)
917–6494; fax (425) 917–6590; has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Material Incorporated by Reference
(i) You must use the service information
contained in Table 1 of this AD to do the
actions required by this AD, as applicable,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1, fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(3) You may review copies of the service
information that is incorporated by reference
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington.
For information on the availability of this
material at the FAA, call 425–227–1221 or
425–227–1152.
(4) You may also review copies of the
service 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.
TABLE 1—MATERIAL INCORPORATED BY REFERENCE
Service Bulletin
Boeing
Boeing
Boeing
Boeing
Revision
Service Bulletin 777–31A0119 ............................................................................................................
Service Bulletin 777–31A0120 ............................................................................................................
Special Attention Service Bulletin 777–31–0097 ................................................................................
Special Attention Service Bulletin 777–31–0098 ................................................................................
Issued in Renton, Washington, on January
13, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–3367 Filed 2–25–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0908; Directorate
Identifier 2007–NM–190–AD; Amendment
39–15788; AD 2009–01–09]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to all Airbus Model A310
series airplanes. That AD currently
requires repetitive detailed inspections
to detect cracks propagating from the
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fastener holes that attach the left- and
right-hand pick-up angles at frame 40 to
the wing lower skin and fuselage panel,
and corrective actions if necessary. This
new AD revises the intervals for
accomplishing the repetitive detailed
inspections and provides for an optional
terminating modification for the
repetitive inspections. This new AD also
revises the applicability of the AD to
remove certain airplanes. This AD
results from mandatory continuing
airworthiness information originated by
an aviation authority of another country
to identify and correct an unsafe
condition on an aviation product. We
are issuing this AD to prevent reduced
structural integrity of the airplane due
to fatigue damage, and consequent
cracking of the pick-up angles at frame
40.
DATES: This AD is effective April 2,
2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 2, 2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
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Date
2
2
3
1
June 12, 2008.
June 12, 2008.
February 22, 2007.
May 3, 2007.
this AD as of February 9, 2001 (66 FR
1031, January 5, 2001).
ADDRESSES: For service information
identified in this AD, contact Airbus
SAS–EAW (Airworthiness Office), 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
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Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that supersedes AD
2000–26–14, amendment 39–12064 (66
FR 1031, January 5, 2001). The existing
AD applies to all Airbus Model A310
series airplanes. That NPRM was
published in the Federal Register on
August 26, 2008 (73 FR 50250). A
correction to that NPRM was published
in the Federal Register on September 8,
2008 (73 FR 51961). That NPRM
proposed to continue to require
repetitive detailed inspections to detect
cracks propagating from the fastener
holes that attach the left- and right-hand
pick-up angles at frame 40 to the wing
lower skin and fuselage panel, and
corrective actions if necessary. That
NPRM also proposed to revise the
intervals for accomplishing the
repetitive detailed inspections and
provided for an optional terminating
modification for the repetitive
inspections. That NPRM also proposed
to revise the applicability of the AD to
remove certain airplanes.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
This AD affects about 68 Model A310
series airplanes of U.S. registry.
The inspections that are required by
AD 2000–26–14 and retained in this AD
take about 2 work hours per airplane, at
an average labor rate of $80 per work
hour. Based on these figures, the
estimated cost of the currently required
actions is $10,880, or $160 per airplane,
per inspection cycle.
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
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
under the criteria of the Regulatory
Flexibility Act.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority for This Rulemaking
Authority: 49 U.S.C. 106(g), 40113, 44701.
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
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14:57 Feb 25, 2009
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–12064 (66 FR
1031, January 5, 2001) and by adding
the following new AD:
■
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8729
2009–01–09 Airbus: Amendment 39–15788.
Docket No. FAA–2008–0908; Directorate
Identifier 2007–NM–190–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective April 2, 2009.
Affected ADs
(b) This AD supersedes AD 2000–26–14.
Applicability
(c) This AD applies to Airbus Model A310
series airplanes, certificated in any category,
except those airplanes modified in-service in
accordance with Airbus Service Bulletin
A310–53–2119, dated October 25, 2005; or
Revision 01, dated February 27, 2007.
Unsafe Condition
(d) This AD results from mandatory
continuing airworthiness information
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. We are
issuing this AD to prevent reduced structural
integrity of the airplane due to fatigue
damage and consequent cracking of the pickup angles at frame 40.
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.
Requirements of AD 2000–26–14
Inspections and Corrective Actions
(f) Perform a detailed inspection to detect
cracks propagating from the fastener holes
that attach the left- and right-hand pick-up
angles at frame 40 to the wing lower skin and
fuselage panel, at the time specified in
paragraph (g), (h), (i), (j), or (k) of this AD,
as applicable. Perform the actions in
accordance with Figure 2, Sheet 1, ‘‘Synoptic
Chart,’’ of Airbus Service Bulletin A310–
53A2111, Revision 01, dated June 21, 2000,
except as provided by paragraph (l) of this
AD.
(1) If no cracking is found during the
inspection required by paragraph (f) of this
AD, repeat the detailed inspection thereafter
at the interval specified in paragraph (f)(1)(i)
or (f)(1)(ii) of this AD, as applicable, except
as provided by paragraph (n) of this AD.
(i) For Model A310–200 series airplanes:
Except as provided by paragraph (i) of this
AD, repeat the inspection thereafter at
intervals not to exceed 1,000 flight cycles or
2,600 flight hours, whichever occurs first.
(ii) For Model A310–300 series airplanes:
Except as provided by paragraphs (i) of this
AD, repeat the inspection thereafter at
intervals not to exceed 850 flight cycles or
2,800 flight hours, whichever occurs first.
(2) If any cracking is found during the
inspection required by paragraph (f) of this
AD, prior to further flight, perform applicable
corrective actions (including repair (drilling
and reaming a crack stop hole in the pickup angle, performing a Rototest inspection
and repetitive detailed inspections at the
time specified in the service bulletin, and
replacing the pick-up angle with a new angle
at the time specified in the service bulletin,
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except as provided by paragraph (o) of this
AD); or immediate replacement of any
cracked angle with a new angle). Perform the
actions and repetitive inspections in
accordance with Figure 2, Sheet 1, ‘‘Synoptic
Chart,’’ of Airbus Service Bulletin A310–
53A2111, Revision 01, dated June 21, 2000,
except as provided by paragraph (l) of this
AD.
Note 1: Accomplishment of the actions
required by paragraph (f) of this AD in
accordance with Airbus Service Bulletin
A310–53A2111, dated April 21, 2000, is
considered to be acceptable for compliance
with the requirements of that paragraph.
Compliance Times
(g) For Model A310–200 series airplanes:
Except as provided by paragraphs (i), (j), and
(k) of this AD, perform the initial inspection
at the later of the times specified in
paragraphs (g)(1) and (g)(2) of this AD.
(1) Prior to the accumulation of 7,900 total
flight cycles or 23,600 total flight hours,
whichever occurs first.
(2) Within 700 flight cycles or 1,200 flight
hours after February 9, 2001 (the effective
date of AD 2000–26–14), whichever occurs
first.
(h) For Model A310–300 series airplanes:
Except as provided by paragraphs (i), (j), and
(k) of this AD, perform the initial inspection
required by paragraph (f) of this AD at the
later of the times specified in paragraphs
(h)(1) and (h)(2) of this AD.
(1) Prior to the accumulation of 6,700 total
flight cycles or 24,700 total flight hours,
whichever occurs first.
(2) Within 700 flight cycles or 1,200 flight
hours after February 9, 2001, whichever
occurs first.
(i) For airplanes that have accumulated
more than 18,000 total flight cycles or 53,000
total flight hours as of February 9, 2001:
Perform the initial inspection required by
paragraph (f) of this AD within 350 flight
cycles or 600 flight hours after February 9,
2001, whichever occurs first. Repeat the
inspection thereafter at intervals not to
exceed 350 flight cycles or 600 flight hours,
whichever occurs first.
(j) For airplanes having manufacturer’s
serial number 0162 through 0326 inclusive,
on which Airbus Service Bulletin A310–53–
2014 has been accomplished prior to
February 9, 2001: The initial inspection
threshold may be counted from the date of
accomplishment of Airbus Service Bulletin
A310–53–2014.
(k) For airplanes on which a pick-up angle
has been replaced: For that pick-up angle
only, the initial inspection threshold may be
counted from the date of installation of the
new pick-up angle.
Note 2: For the purposes of this AD, a
detailed inspection is defined as: ‘‘An
intensive visual examination of a specific
structural area, system, installation, or
assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.’’
New Requirements of This AD
New Revisions of Service Bulletin
(l) As of the effective date of this AD, use
only the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310–53–
2111, Revision 03, dated May 21, 2007, to do
the inspections and corrective actions
required by paragraph (f) of this AD; except
where Figure 2 Sheet 2 of Airbus Mandatory
Service Bulletin A310–53–2111, Revision 03,
dated May 21, 2007, specifies actions for
crack length of ‘‘<54 mm (2.126 in.)’’ and
‘‘<69 mm (2.716 in.),’’ this AD requires the
corresponding actions for crack lengths less
than or equal to those measurements.
(m) Inspections and applicable corrective
actions done before the effective date of this
AD in accordance with Airbus Mandatory
Service Bulletin A310–53–2111, Revision 02,
dated October 25, 2005, are acceptable for
compliance with the requirements of
paragraph (f) of this AD.
Revised Repetitive Intervals for Detailed
Inspections
(n) As of the effective date of this AD,
repeat the detailed inspections for no crack
findings required by paragraph (f)(1)(i),
(f)(1)(ii), or (i) of this AD, as applicable, at the
applicable times specified in Table 1 of this
AD, until the modification specified in
paragraph (p) of this AD is done.
TABLE 1—REVISED REPETITIVE INTERVALS FOR CERTAIN DETAILED INSPECTIONS
For model—
Repeat the inspection at the later of the following times—
And thereafter at intervals not to
exceed—
(1) A310–200 series airplanes .......
Within 950 flight cycles or 1,900
flight hours since the last inspection required by paragraph
(f)(1)(i) or (i) of this AD, whichever occurs first.
Within 50 flight cycles or 250 flight
hours after the effective date of
this AD, whichever occurs first.
950 flight cycles or 1,900 flight
hours, whichever occurs first.
(2) A310–300 series
(short range).
airplanes
Within 900 flight cycles or 2,550
flight hours since the last inspection required by paragraph
(f)(1)(ii) or (i) of this AD, whichever occurs first.
Within 50 flight cycles or 250 flight
hours after the effective date of
this AD, whichever occurs first.
900 flight cycles or 2,550 flight
hours, whichever occurs first.
(3) A310–300
(long range).
airplanes
Within 800 flight cycles or 4,000
flight hours since the last inspection required by paragraph
(f)(1)(ii) or (i) of this AD, whichever occurs first.
Within 50 flight cycles or 250 flight
hours after the effective date of
this AD, whichever occurs first.
800 flight cycles or 4,000 flight
hours, whichever occurs first.
series
Revised Threshold for Replacing the PickUp Angles
(o) As of the effective date of this AD, do
the replacement of the pick-up angle required
by paragraph (f)(2) of this AD, at the
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applicable time specified in Table 2 of this
AD.
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Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations
TABLE 2—REVISED THRESHOLDS FOR REPLACING PICK-UP ANGLES
For model—
Replace at the earlier of the following times—
(1) A310–200 series airplanes ..........................
At the time specified in paragraph (f)(2) of this
AD for replacing the pick-up angle.
Within 1,500 flight cycles or 3,000 flight hours
since the last detailed inspection, or within
30 days after the effective date of this AD,
whichever occurs later.
(2) A310–300 series airplanes (short range) ....
At the time specified in paragraph (f)(2) of this
AD for replacing the pick-up angle.
Within 1,600 flight cycles or 4,600 flight hours
since the last detailed inspection, or within
30 days after the effective date of this AD,
whichever occurs later.
(3) A310–300 series airplanes (long range) .....
At the time specified in paragraph (f)(2) of this
AD for replacing the pick-up angle.
Within 1,400 flight cycles or 7,200 flight hours
since the last detailed inspection, or within
30 days after the effective date of this AD,
whichever occurs later.
Optional Terminating Modification
European Aviation Safety Agency (EASA) (or
its delegated agent).
(r) Actions done before the effective date of
this AD in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–53–2119, dated
October 25, 2005, are acceptable for
compliance with the corresponding
requirements of paragraph (p) of this AD.
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(p) Remove the existing pick-up angles and
install a reinforced doubler between frames
(FR) FR40 and FR41, and perform applicable
related investigative and corrective actions
by accomplishing all the applicable actions
specified in the Accomplishment
Instructions of Airbus Service Bulletin A310–
53–2119, Revision 01, dated February 27,
2007; except as provided by paragraph (q) of
this AD. Accomplishing these actions ends
the repetitive inspections required by this
AD.
(q) If any crack is detected and Airbus
Service Bulletin A310–53–2119, Revision 01,
dated February 27, 2007, specifies to contact
Airbus: Before further flight, repair the crack
using a method approved by either the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
Alternative Methods of Compliance
(AMOCs)
(s) The Manager, International Branch,
ANM–116, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send
information to ATTN: Dan Rodina,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2125; fax (425) 227–1149. Before using
Related Information
(t) EASA airworthiness directive 2007–
0184, dated July 3, 2007, also addresses the
subject of this AD.
Material Incorporated by Reference
(u) You must use the service information
identified in Table 3 of this AD to do the
actions required by this AD, unless the AD
specifies otherwise. If you do the optional
terminating modification provided in this
AD, you must use Airbus Service Bulletin
A310–53–2119, Revision 01, including
Appendix 01, dated February 27, 2007, to do
the optional terminating modification.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE FOR ACTIONS REQUIRED BY THIS AD
Revision
level
Service bulletin
Airbus Service Bulletin A310–53A2111, including Appendix 01 .....................................................................
Airbus Mandatory Service Bulletin A310–53–2111, including Appendix 01 ...................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information identified in Table 4
01
03
Date
June 21, 2000.
May 21, 2007.
of this AD under 5 U.S.C. 552(a) and 1 CFR
part 51.
TABLE 4—NEW MATERIAL INCORPORATED BY REFERENCE
Revision
level
Service bulletin
Airbus Mandatory Service Bulletin A310–53–2111, including Appendix 01 ...................................................
A310–53–2119, including Appendix 01 ...........................................................................................................
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Airbus Service Bulletin A310–
53A2111, Revision 01, including Appendix
1, dated June 21, 2000, on February 9, 2001
(66 FR 1031, January 5, 2001).
(3) For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 1 Rond Point Maurice
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Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail: account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(4) You may review copies of the service
information that is incorporated by reference
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
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03
01
Date
May 21, 2007.
February 27, 2007.
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(5) You may also review copies of the
service 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/
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code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–3765 Filed 2–25–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0034; Directorate
Identifier 2007–NM–082–AD; Amendment
39–15797; AD 2009–02–07]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited
(Jetstream) Model 4101 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to certain British Aerospace
(Jetstream) Model 4100 series airplanes.
The existing AD currently requires an
eddy current conductivity test to
measure the conductivity of the upper
splice plate of the wing, and related
investigative and corrective actions if
necessary. This AD revises the
applicability to include additional
airplanes. This AD results from reports
of exfoliation corrosion of the upper
splice plate of the wing. We are issuing
this AD to detect and correct such
corrosion, which could result in
reduced structural integrity of the
airplane.
DATES: This AD becomes effective
March 13, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications as of March 13,
2009.
On September 23, 1998 (63 FR 44371,
August 19, 1998), the Director of the
Federal Register approved the
incorporation by reference of certain
other publications.
We must receive comments on this
AD by March 30, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
VerDate Nov<24>2008
14:57 Feb 25, 2009
Jkt 217001
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact BAE Systems Regional
Aircraft, 13850 Mclearen Road,
Herndon, Virginia 20171; telephone
703–736–1080; e-mail
raebusiness@baesystems.com; Internet
https://www.baesystems.com/Businesses/
RegionalAircraft/index.htm.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1175; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
On August 11, 1998, the FAA issued
AD 98–17–12, amendment 39–10714 (63
FR 44371, August 19, 1998). That AD
applies to certain British Aerospace
(Jetstream) Model 4100 series airplanes.
That AD requires an eddy current
conductivity test to measure the
conductivity of the upper splice plate of
the wing, and follow-on actions if
necessary. That AD resulted from
issuance of mandatory continuing
airworthiness information from another
civil airworthiness authority (British
airworthiness directive 005–03–97). The
actions specified in AD 98–17–12 are
intended to detect and correct corrosion
of the upper splice plate of the wing,
which could result in reduced structural
integrity of the airplane.
Actions Since AD Was Issued
Since we issued AD 98–17–12, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
PO 00000
Frm 00030
Fmt 4700
Sfmt 4700
for the Member States of the European
Community, issued Airworthiness
Directive 2007–0056, dated March 1,
2007. The EASA Airworthiness
Directive superseded British
airworthiness directive 005–03–97 by
adding airplanes with construction
numbers 41102 through 41104. The
EASA advises that those airplanes might
also be subject to the identified unsafe
condition.
Relevant Service Information
AD 98–17–12 requires
accomplishment of British Aerospace
Regional Aircraft Service Bulletins J41–
57–019, Revision 1, dated November 26,
1997; J41–57–020, dated March 20,
1997; and J41–57–021, dated May 7,
1998. BAE Systems (Operations)
Limited has issued Revision 1 of Service
Bulletin J41–57–020, dated July 3, 2006;
and Revision 4 of Service Bulletin J41–
57–021, dated January 16, 2003. BAE
Systems (Operations) Limited Service
Bulletin J41–57–020, Revision 1, adds
the three airplanes referenced above.
The revised service bulletins specify no
new actions for any affected airplanes.
The EASA mandated the service
information and issued airworthiness
directive 2007–0056, dated March 1,
2007 (referred to after this as ‘‘the
MCAI’’), to ensure the continued
airworthiness of these airplanes in the
European Union.
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Therefore, we are issuing this AD to
detect and correct such corrosion,
which could result in reduced structural
integrity of the airplane. This new AD
retains the requirements of the existing
AD, and revises the applicability to
include additional airplanes.
Explanation of Additional Change to
Applicability
We have further revised the
applicability of the existing AD to
identify model designations as
published in the most recent type
certificate data sheet for the affected
models.
E:\FR\FM\26FER1.SGM
26FER1
]]>Agencies
[Federal Register Volume 74, Number 37 (Thursday, February 26, 2009)]
[Rules and Regulations]
[Pages 8728-8732]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3765]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0908; Directorate Identifier 2007-NM-190-AD;
Amendment 39-15788; AD 2009-01-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to all Airbus Model A310 series airplanes. That AD
currently requires repetitive detailed inspections to detect cracks
propagating from the fastener holes that attach the left- and right-
hand pick-up angles at frame 40 to the wing lower skin and fuselage
panel, and corrective actions if necessary. This new AD revises the
intervals for accomplishing the repetitive detailed inspections and
provides for an optional terminating modification for the repetitive
inspections. This new AD also revises the applicability of the AD to
remove certain airplanes. This AD results from mandatory continuing
airworthiness information originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. We are issuing this AD to prevent reduced structural
integrity of the airplane due to fatigue damage, and consequent
cracking of the pick-up angles at frame 40.
DATES: This AD is effective April 2, 2009.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 2,
2009.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
February 9, 2001 (66 FR 1031, January 5, 2001).
ADDRESSES: For service information identified in this AD, contact
Airbus SAS-EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail account.airworth-eas@airbus.com; Internet https://
www.airbus.com.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116,
[[Page 8729]]
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness directive (AD) that supersedes AD
2000-26-14, amendment 39-12064 (66 FR 1031, January 5, 2001). The
existing AD applies to all Airbus Model A310 series airplanes. That
NPRM was published in the Federal Register on August 26, 2008 (73 FR
50250). A correction to that NPRM was published in the Federal Register
on September 8, 2008 (73 FR 51961). That NPRM proposed to continue to
require repetitive detailed inspections to detect cracks propagating
from the fastener holes that attach the left- and right-hand pick-up
angles at frame 40 to the wing lower skin and fuselage panel, and
corrective actions if necessary. That NPRM also proposed to revise the
intervals for accomplishing the repetitive detailed inspections and
provided for an optional terminating modification for the repetitive
inspections. That NPRM also proposed to revise the applicability of the
AD to remove certain airplanes.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed.
Costs of Compliance
This AD affects about 68 Model A310 series airplanes of U.S.
registry.
The inspections that are required by AD 2000-26-14 and retained in
this AD take about 2 work hours per airplane, at an average labor rate
of $80 per work hour. Based on these figures, the estimated cost of the
currently required actions is $10,880, or $160 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 Findings
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 under the criteria
of the Regulatory Flexibility Act.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The FAA amends Sec. 39.13 by removing amendment 39-12064 (66 FR
1031, January 5, 2001) and by adding the following new AD:
2009-01-09 Airbus: Amendment 39-15788. Docket No. FAA-2008-0908;
Directorate Identifier 2007-NM-190-AD.
Effective Date
(a) This airworthiness directive (AD) is effective April 2,
2009.
Affected ADs
(b) This AD supersedes AD 2000-26-14.
Applicability
(c) This AD applies to Airbus Model A310 series airplanes,
certificated in any category, except those airplanes modified in-
service in accordance with Airbus Service Bulletin A310-53-2119,
dated October 25, 2005; or Revision 01, dated February 27, 2007.
Unsafe Condition
(d) This AD results from mandatory continuing airworthiness
information originated by an aviation authority of another country
to identify and correct an unsafe condition on an aviation product.
We are issuing this AD to prevent reduced structural integrity of
the airplane due to fatigue damage and consequent cracking of the
pick-up angles at frame 40.
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.
Requirements of AD 2000-26-14
Inspections and Corrective Actions
(f) Perform a detailed inspection to detect cracks propagating
from the fastener holes that attach the left- and right-hand pick-up
angles at frame 40 to the wing lower skin and fuselage panel, at the
time specified in paragraph (g), (h), (i), (j), or (k) of this AD,
as applicable. Perform the actions in accordance with Figure 2,
Sheet 1, ``Synoptic Chart,'' of Airbus Service Bulletin A310-
53A2111, Revision 01, dated June 21, 2000, except as provided by
paragraph (l) of this AD.
(1) If no cracking is found during the inspection required by
paragraph (f) of this AD, repeat the detailed inspection thereafter
at the interval specified in paragraph (f)(1)(i) or (f)(1)(ii) of
this AD, as applicable, except as provided by paragraph (n) of this
AD.
(i) For Model A310-200 series airplanes: Except as provided by
paragraph (i) of this AD, repeat the inspection thereafter at
intervals not to exceed 1,000 flight cycles or 2,600 flight hours,
whichever occurs first.
(ii) For Model A310-300 series airplanes: Except as provided by
paragraphs (i) of this AD, repeat the inspection thereafter at
intervals not to exceed 850 flight cycles or 2,800 flight hours,
whichever occurs first.
(2) If any cracking is found during the inspection required by
paragraph (f) of this AD, prior to further flight, perform
applicable corrective actions (including repair (drilling and
reaming a crack stop hole in the pick-up angle, performing a
Rototest inspection and repetitive detailed inspections at the time
specified in the service bulletin, and replacing the pick-up angle
with a new angle at the time specified in the service bulletin,
[[Page 8730]]
except as provided by paragraph (o) of this AD); or immediate
replacement of any cracked angle with a new angle). Perform the
actions and repetitive inspections in accordance with Figure 2,
Sheet 1, ``Synoptic Chart,'' of Airbus Service Bulletin A310-
53A2111, Revision 01, dated June 21, 2000, except as provided by
paragraph (l) of this AD.
Note 1: Accomplishment of the actions required by paragraph (f)
of this AD in accordance with Airbus Service Bulletin A310-53A2111,
dated April 21, 2000, is considered to be acceptable for compliance
with the requirements of that paragraph.
Compliance Times
(g) For Model A310-200 series airplanes: Except as provided by
paragraphs (i), (j), and (k) of this AD, perform the initial
inspection at the later of the times specified in paragraphs (g)(1)
and (g)(2) of this AD.
(1) Prior to the accumulation of 7,900 total flight cycles or
23,600 total flight hours, whichever occurs first.
(2) Within 700 flight cycles or 1,200 flight hours after
February 9, 2001 (the effective date of AD 2000-26-14), whichever
occurs first.
(h) For Model A310-300 series airplanes: Except as provided by
paragraphs (i), (j), and (k) of this AD, perform the initial
inspection required by paragraph (f) of this AD at the later of the
times specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Prior to the accumulation of 6,700 total flight cycles or
24,700 total flight hours, whichever occurs first.
(2) Within 700 flight cycles or 1,200 flight hours after
February 9, 2001, whichever occurs first.
(i) For airplanes that have accumulated more than 18,000 total
flight cycles or 53,000 total flight hours as of February 9, 2001:
Perform the initial inspection required by paragraph (f) of this AD
within 350 flight cycles or 600 flight hours after February 9, 2001,
whichever occurs first. Repeat the inspection thereafter at
intervals not to exceed 350 flight cycles or 600 flight hours,
whichever occurs first.
(j) For airplanes having manufacturer's serial number 0162
through 0326 inclusive, on which Airbus Service Bulletin A310-53-
2014 has been accomplished prior to February 9, 2001: The initial
inspection threshold may be counted from the date of accomplishment
of Airbus Service Bulletin A310-53-2014.
(k) For airplanes on which a pick-up angle has been replaced:
For that pick-up angle only, the initial inspection threshold may be
counted from the date of installation of the new pick-up angle.
Note 2: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
New Requirements of This AD
New Revisions of Service Bulletin
(l) As of the effective date of this AD, use only the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2111, Revision 03, dated May 21, 2007, to do the inspections
and corrective actions required by paragraph (f) of this AD; except
where Figure 2 Sheet 2 of Airbus Mandatory Service Bulletin A310-53-
2111, Revision 03, dated May 21, 2007, specifies actions for crack
length of ``<54 mm (2.126 in.)'' and ``<69 mm (2.716 in.),'' this AD
requires the corresponding actions for crack lengths less than or
equal to those measurements.
(m) Inspections and applicable corrective actions done before
the effective date of this AD in accordance with Airbus Mandatory
Service Bulletin A310-53-2111, Revision 02, dated October 25, 2005,
are acceptable for compliance with the requirements of paragraph (f)
of this AD.
Revised Repetitive Intervals for Detailed Inspections
(n) As of the effective date of this AD, repeat the detailed
inspections for no crack findings required by paragraph (f)(1)(i),
(f)(1)(ii), or (i) of this AD, as applicable, at the applicable
times specified in Table 1 of this AD, until the modification
specified in paragraph (p) of this AD is done.
Table 1--Revised Repetitive Intervals for Certain Detailed Inspections
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
For model-- Repeat the inspection at the later of the And thereafter at
following times-- intervals not to
exceed--
----------------------------------------------------------------------------------------------------------------
(1) A310-200 series airplanes........ Within 950 flight Within 50 flight cycles 950 flight cycles or
cycles or 1,900 flight or 250 flight hours 1,900 flight hours,
hours since the last after the effective whichever occurs
inspection required by date of this AD, first.
paragraph (f)(1)(i) or whichever occurs first.
(i) of this AD,
whichever occurs first.
----------------------------------------------------------------------------------------------------------------
(2) A310-300 series airplanes (short Within 900 flight Within 50 flight cycles 900 flight cycles or
range). cycles or 2,550 flight or 250 flight hours 2,550 flight hours,
hours since the last after the effective whichever occurs
inspection required by date of this AD, first.
paragraph (f)(1)(ii) whichever occurs first.
or (i) of this AD,
whichever occurs first.
----------------------------------------------------------------------------------------------------------------
(3) A310-300 series airplanes (long Within 800 flight Within 50 flight cycles 800 flight cycles or
range). cycles or 4,000 flight or 250 flight hours 4,000 flight hours,
hours since the last after the effective whichever occurs
inspection required by date of this AD, first.
paragraph (f)(1)(ii) whichever occurs first.
or (i) of this AD,
whichever occurs first.
----------------------------------------------------------------------------------------------------------------
Revised Threshold for Replacing the Pick-Up Angles
(o) As of the effective date of this AD, do the replacement of
the pick-up angle required by paragraph (f)(2) of this AD, at the
applicable time specified in Table 2 of this AD.
[[Page 8731]]
Table 2--Revised Thresholds for Replacing Pick-Up Angles
------------------------------------------------------------------------
------------------------------------------------------------------------
For model-- Replace at the earlier of the
following times--
------------------------------------------------------------------------
(1) A310-200 series airplanes... At the time Within 1,500
specified in flight cycles or
paragraph (f)(2) 3,000 flight
of this AD for hours since the
replacing the last detailed
pick-up angle. inspection, or
within 30 days
after the
effective date of
this AD,
whichever occurs
later.
------------------------------------------------------------------------
(2) A310-300 series airplanes At the time Within 1,600
(short range). specified in flight cycles or
paragraph (f)(2) 4,600 flight
of this AD for hours since the
replacing the last detailed
pick-up angle. inspection, or
within 30 days
after the
effective date of
this AD,
whichever occurs
later.
------------------------------------------------------------------------
(3) A310-300 series airplanes At the time Within 1,400
(long range). specified in flight cycles or
paragraph (f)(2) 7,200 flight
of this AD for hours since the
replacing the last detailed
pick-up angle. inspection, or
within 30 days
after the
effective date of
this AD,
whichever occurs
later.
------------------------------------------------------------------------
Optional Terminating Modification
(p) Remove the existing pick-up angles and install a reinforced
doubler between frames (FR) FR40 and FR41, and perform applicable
related investigative and corrective actions by accomplishing all
the applicable actions specified in the Accomplishment Instructions
of Airbus Service Bulletin A310-53-2119, Revision 01, dated February
27, 2007; except as provided by paragraph (q) of this AD.
Accomplishing these actions ends the repetitive inspections required
by this AD.
(q) If any crack is detected and Airbus Service Bulletin A310-
53-2119, Revision 01, dated February 27, 2007, specifies to contact
Airbus: Before further flight, repair the crack using a method
approved by either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA) (or its delegated agent).
(r) Actions done before the effective date of this AD in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-53-2119, dated October 25, 2005, are acceptable for
compliance with the corresponding requirements of paragraph (p) of
this AD.
Alternative Methods of Compliance (AMOCs)
(s) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Dan
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
Related Information
(t) EASA airworthiness directive 2007-0184, dated July 3, 2007,
also addresses the subject of this AD.
Material Incorporated by Reference
(u) You must use the service information identified in Table 3
of this AD to do the actions required by this AD, unless the AD
specifies otherwise. If you do the optional terminating modification
provided in this AD, you must use Airbus Service Bulletin A310-53-
2119, Revision 01, including Appendix 01, dated February 27, 2007,
to do the optional terminating modification.
Table 3--Material Incorporated by Reference for Actions required by This
AD
------------------------------------------------------------------------
Revision
Service bulletin level Date
------------------------------------------------------------------------
Airbus Service Bulletin A310- 01 June 21, 2000.
53A2111, including Appendix
01.
Airbus Mandatory Service 03 May 21, 2007.
Bulletin A310-53-2111,
including Appendix 01.
------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the service information identified in
Table 4 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.
Table 4--New Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Service bulletin level Date
------------------------------------------------------------------------
Airbus Mandatory Service 03 May 21, 2007.
Bulletin A310-53-2111,
including Appendix 01.
A310-53-2119, including 01 February 27, 2007.
Appendix 01.
------------------------------------------------------------------------
(2) The Director of the Federal Register previously approved the
incorporation by reference of Airbus Service Bulletin A310-53A2111,
Revision 01, including Appendix 1, dated June 21, 2000, on February
9, 2001 (66 FR 1031, January 5, 2001).
(3) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(4) You may review copies of the service information that is
incorporated by reference at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For
information on the availability of this material at the FAA, call
425-227-1221 or 425-227-1152.
(5) You may also review copies of the service 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/
[[Page 8732]]
code--of--federal--regulations/ibr--locations.html.
Issued in Renton, Washington, on December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E9-3765 Filed 2-25-09; 8:45 am]
BILLING CODE 4910-13-P
