Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes, 14751-14759 [E9-7267]
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14751
Federal Register / Vol. 74, No. 61 / Wednesday, April 1, 2009 / Proposed Rules
TABLE—ESTIMATED COSTS
Action
Work hours
Average labor
rate per hour
Parts
Cost
Number of
U.S.-registered
airplanes
Fleet cost
Replacement ............................................
25
$80
$60,670
$62,670
249
$15,604,830
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.
the FAA proposes to amend 14 CFR part
39 as follows:
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
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PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Boeing: Docket No. FAA–2009–0293;
Directorate Identifier 2008–NM–221–AD.
Comments Due Date
(a) We must receive comments by May 18,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
100, –100B, –100B SUD, –200B, –200C,
–200F, –300, –400, –400D, –400F, and 747SR
series airplanes, certificated in any category;
as identified in Boeing Special Attention
Service Bulletin 747–27–2422, dated October
30, 2008.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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:
Douglas Tsuji, Aerospace Engineer, Systems
and Equipment Branch, ANM–130S, FAA,
Seattle Aircraft Certification Office, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6487; fax
(425) 917–6590.
(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 principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
Issued in Renton, Washington, on March
18, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–7273 Filed 3–31–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Unsafe Condition
(e) This AD results from reports of the
inboard trailing edge (TE) flaps blowing back
due to the failure of a transmission carbon
disk no-back brake. The no-back brake did
not hold the flaps in the commanded
position. The Federal Aviation
Administration is issuing this AD to prevent
a decrease of the aerodynamic controllability
of the airplane, which could adversely affect
the airplane’s continued safe flight and
landing.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Corrective Action
(g) Within 5 years after the effective date
of this AD, replace the trailing edge flap
transmission no-back brakes with skewed
roller no-back brakes at the trailing edge flap
transmission, positions 4 and 5, in
accordance with Boeing Special Attention
Service Bulletin 747–27–2422, dated October
30, 2008.
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14 CFR Part 39
[Docket No. FAA–2009–0292; Directorate
Identifier 2008–NM–011–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300, A310, and A300–600 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Airbus Model A300 and A310 series
airplanes. The existing AD currently
requires replacement of the nose
landing gear drag strut upper
attachment pin. This proposed AD
would require revising the
Airworthiness Limitations section (ALS)
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of the Instructions for Continued
Airworthiness (ICA) to require
additional life limits and/or
replacements for certain main landing
gear and nose landing gear components,
and would also expand the
applicability. This proposed AD results
from revisions to the ALS of the ICA to
include new or more restrictive life
limits and/or replacements. We are
proposing this AD to ensure the
continued structural integrity of these
airplanes.
DATES: We must receive comments on
this proposed AD by May 1, 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.
• 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 proposed 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. You
may review copies of the referenced
service information 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.
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 proposed 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: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
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1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1622; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2009–0292; Directorate Identifier
2008–NM–011–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On July 21, 1987, we issued AD 87–
16–06, amendment 39–5692 (52 FR
28241, July 29, 1987), for certain Airbus
Model A300 and A310 series airplanes.
That AD requires replacement of the
nose landing gear drag strut upper
attachment pin. That AD resulted from
reports of pins which were found to be
improperly manufactured. We issued
that AD to prevent failure of the pin and
collapse of the nose landing gear.
Actions Since Existing AD Was Issued
Since we issued AD 87–16–06, the
manufacturer has revised the
Airworthiness Limitations Section
(ALS) of the Instructions for Continued
Airworthiness (ICA) to include new or
more restrictive life limits and
replacements for the main landing gear
and the nose landing gear. These new
limits affect the replacement of the
upper attachment pin for the nose
landing gear drag strut that was the
subject of AD 87–16–06.
In addition, European Aviation Safety
Agency (EASA) Airworthiness Directive
2007–0293, dated November 29, 2007,
which is parallel to this proposed AD,
includes Model A300–600 series
airplanes. Those airplane models were
not included in AD 87–16–06.
Relevant Service Information
Airbus has issued the following
revisions to the ALS of the ICA. These
documents provide each mandatory
replacement time, structural inspection
interval, and related structural
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inspection procedures or other
procedures (e.g., modifications).
• For Model A300 Series Airplanes:
‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated fatigue lives’’ of
Part 1, ‘‘Safe Life Airworthiness
Limitation Items,’’ dated September 6,
2007.
• For Model A300–600 Series
Airplanes: ‘‘Sub-part 1–2: Life Limits,’’
and ‘‘Sub-part 1–3: Demonstrated
fatigue lives’’ of Part 1, ‘‘Safe Life
Airworthiness Limitation Items,’’ dated
December 21, 2006.
• For Model A310 Series Airplanes:
‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated fatigue lives’’ of
Part 1, ‘‘Safe Life Airworthiness
Limitation Items,’’ dated December 21,
2006.
Airbus has also issued Section 05–10–
00, Revision 28, dated February 27,
1998, of Chapter 5, ‘‘Service Life Limits
and Maintenance Checks,’’ of the A300
Aircraft Maintenance Manual. Section
05–10–00 includes life limit values for
the nose and main landing gears. This
document is an alternate source for the
life limits defined in Part 1, ‘‘Safe Life
Airworthiness Limitation Items,’’ dated
September 6, 2007, of the ALS, for
Model A300 series airplanes.
Airbus has also issued Service
Information Letter (SIL) 32–118,
Revision 02, dated October 24, 2007.
This SIL gives instructions for
calculating the life limit of main or nose
landing gear parts where the history of
accumulated landings is partial or
unknown, or where the history of
application details (airplane type,
model, weight variant, etc.) is partial or
unknown.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. EASA mandated the service
information and issued Airworthiness
Directive 2007–0292, dated November
29, 2007, to ensure the continued
airworthiness of these airplanes in the
European Union.
Other Relevant Rulemaking
On January 11, 1984, we issued AD
84–02–04 (49 FR 2746, January 23,
1984), for certain Airbus Model A300 B2
and B4 series airplanes. That AD
requires inspection of main landing gear
hinge arms for corrosion and cracks, and
repair or modifications if needed. That
AD also requires replacement of the
main landing gear shock absorber
sliding rod attachment fitting. That AD
resulted from corrosion and cracks
found on these components. We issued
that AD to prevent landing gear failure.
The actions specified in paragraph (h)
of this proposed AD would satisfy the
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Federal Register / Vol. 74, No. 61 / Wednesday, April 1, 2009 / Proposed Rules
requirements of paragraph A. of AD 84–
02–04. There are no actions in this
proposed AD that would satisfy the
requirements of paragraphs B. and C. of
AD 84–02–04.
FAA’s Determination and Requirements
of the Proposed 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.
This proposed AD would supersede
AD 87–16–06 and would retain the
requirements of that existing AD. This
proposed AD would also add airplanes
to the applicability and require revising
the ALS of the ICA to incorporate
additional life limits and/or structural
inspections for certain main landing
gear and nose landing gear components.
Change to Existing AD
This proposed AD would retain the
requirements of AD 87–16–06. Since AD
87–16–06 was issued, the AD format has
been revised. As a result, the
corresponding paragraph identifiers
have changed in this proposed AD, and
paragraph (g) of this proposed AD
corresponds to paragraph A. of AD 87–
16–06.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Replacement (required by AD 87–16–06)
Revision (new proposed action) ..............
7
1
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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Average labor
rate per hour
Work hours
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Parts
$80
80
$3,300
0
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by Reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–5692 (52
FR 28241, July 29, 1987) and adding the
following new airworthiness directive
(AD):
Airbus: Docket No. FAA–2009–0292;
Directorate Identifier 2008–NM–011–AD.
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Cost per
airplane
$3,860
80
Number of
U.S.-registered
airplanes
94
238
Fleet cost
$362,840
19,040
Comments Due Date
(a) The FAA must receive comments on
this AD action by May 1, 2009.
Affected ADs
(b) This AD supersedes AD 87–16–06.
Applicability
(c) This AD applies to all Airbus Model
A300, A310, and A300–600 series airplanes,
certificated in any category.
Subject
(d) Air Transport Association (ATA) of
America Code 32: Landing Gear.
Unsafe Condition
(e) This AD results from revisions to the
Airworthiness Limitations section (ALS) of
the Instructions for Continued Airworthiness
(ICA) to include new or more restrictive life
limits and/or replacements. We are issuing
this AD to ensure the continued structural
integrity of these airplanes.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new replacements. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these replacements,
the operator may not be able to accomplish
the replacements described in the revisions.
In this situation, to comply with 14 CFR
91.403(c), the operator must request approval
for an alternative method of compliance
according to paragraph (l) of this AD. The
request should include a description of
changes to the required replacements that
will ensure the continued operational safety
of the airplane.
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Restatement of the Requirements of AD 87–
16–06
(g) For Model A300 and A310 Series
Airplanes: Prior to the accumulation of
16,000 landings, or within the next 2,000
landings after September 3, 1987 (the
effective date of AD 87–16–06), whichever
occurs later, replace the nose landing gear
drag strut upper attachment pin in
accordance with Airbus Service Bulletin
A300–32–374, Revision 1, dated July 15,
1986 (applicable to Model A300 airplanes);
or A310–32–2023, Revision 2, dated
November 14, 1986 (applicable to Model
A310 airplanes).
New Requirements of This AD
ALS Revision
(h) For Model A300, A310, and A300–600
Series Airplanes: Within 3 months after the
effective date of this AD, revise the ALS of
the ICA to incorporate the applicable
document listed in paragraph (h)(1), (h)(2), or
(h)(3) of this AD. Accomplishing the actions
specified in the applicable document satisfies
the requirements of paragraph A. of AD 84–
02–04, amendment 39–4795.
(1) For Model A300 Series Airplanes:
Incorporate the document listed in paragraph
(h)(1)(i) or (h)(1)(ii) of this AD.
(i) Section 05–10–00, Revision 28, dated
February 27, 1998, of Chapter 5, ‘‘Service Life
Limits and Maintenance Checks,’’ of the
Airbus A300 Aircraft Maintenance Manual,
except that the parts listed in Table 1 of this
AD are subject to the life limits defined in
the document listed in paragraph (h)(1)(ii) of
this AD.
(ii) ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated fatigue lives’’ of Part
1, ‘‘Safe Life Airworthiness Limitation
Items,’’ dated September 6, 2007, of the
Airbus A300 ALS.
TABLE 1—PARTS SUBJECT TO THE LIFE LIMITS SPECIFIED IN THE DOCUMENT IDENTIFIED IN PARAGRAPH (H)(1)(II) OF THIS
AD
Part Number (P/N)
P/N
P/N
P/N
P/N
Part name
C61643–2, P/N C61643–4, P/N C61643–5 ......................................
A32210001205xx ...............................................................................
C62037–1 ..........................................................................................
196–0328–501 ...................................................................................
(2) For Model A310 Series Airplanes:
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
‘‘Sub-part 1–3: Demonstrated fatigue lives’’ of
Part 1, ‘‘Safe Life Airworthiness Limitation
Items,’’ dated December 21, 2006, of the
Airbus A310 ALS.
(3) For Model A300–600 Series Airplanes:
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
‘‘Sub-part 1–3: Demonstrated fatigue lives’’ of
Part 1, ‘‘Safe Life Airworthiness Limitation
Items,’’ dated December 21, 2006, of the
Airbus A300–600 ALS.
Initial Compliance Times and Repetitive
Inspections
(i) Do the replacement at the applicable
time specified in paragraph (i)(1) or (i)(2) of
this AD, except as provided by paragraph (j)
of this AD. The replacement must be done
thereafter within the interval specified in the
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Main landing gear (MLG) shock absorber end fitting.
Nose landing gear (NLG) pintle pin.
NLG shock absorber bottom.
Cross beam (Pratt & Whitney forward engine mount).
applicable document identified in paragraph
(h)(1), (h)(2), or (h)(3) of this AD.
(1) For any life limitation/task that has
been complied with before the effective date
of this AD in accordance with the applicable
document listed in paragraph (h)(1), (h)(2), or
(h)(3) of this AD, or in accordance with
paragraph (g) of this AD, use the last
accomplishment of each limitation/task as a
starting point for accomplishing each
corresponding limitation/task required by
this AD.
(2) For any life limitation/task that has not
been complied with before the effective date
of this AD in accordance with the applicable
document listed in paragraphs (h)(1), (h)(2),
and (h)(3) of this AD, or in accordance with
paragraph (g) of this AD, the initial
compliance time starts from the date of initial
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entry into service as defined in the applicable
document.
Special Compliance Times
(j) For any airplane on which the history
of accumulated landings is partial or
unknown, or where the history of application
details (airplane type, model, weight variant,
etc.) is partial or unknown, with or without
using the information in Airbus Service
Information Letter 32–118, Revision 02,
dated October 24, 2007: Parts listed in Figure
1 of this AD must be replaced at the
associated compliance time. The replacement
must be done thereafter at the interval
specified in the applicable document(s)
specified in paragraphs (h)(1), (h)(2), and
(h)(3) of this AD.
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Federal Register / Vol. 74, No. 61 / Wednesday, April 1, 2009 / Proposed Rules
(k) Except as provided by paragraph (l) of
this AD, after accomplishing the actions
specified in paragraphs (h), (i), and (j) of this
AD, no alternative replacements, replacement
intervals, or limitations may be used.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, Manager, ANM–116,
International Branch, Transport Airplane
Directorate, 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: Tom Stafford,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1622; fax (425) 227–1149.
(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 principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
Related Information
(m) European Aviation Safety Agency
(EASA) Airworthiness Directive 2007–0293,
dated November 29, 2007, also addresses the
subject of this AD.
Issued in Renton, Washington, on March
12, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–7267 Filed 3–31–09; 8:45 am]
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ENVIRONMENTAL PROTECTION
AGENCY
40 CFR Part 52
[EPA–R06–OAR–2008–0509; FRL–8788–7]
Approval and Promulgation of
Implementation Plans; New Mexico;
Albuquerque/Bernalillo County
AGENCY: Environmental Protection
Agency (EPA).
ACTION: Proposed rule.
SUMMARY: EPA is proposing to approve
a revision to the New Mexico
Albuquerque/Bernalillo County State
Implementation Plan (SIP). This
revision replaces Regulation 8, Airborne
Particulate Matter, with NMAC
20.11.20, Fugitive Dust Control. This
rulemaking action is being taken under
section 110 of the Clean Air Act (CAA).
DATES: Written comments must be
received on or before May 1, 2009.
ADDRESSES: Comments may be mailed to
Mr. Guy Donaldson, Chief, Air Planning
Section (6PD–L), Environmental
Protection Agency, 1445 Ross Avenue,
Suite 1200, Dallas, Texas 75202–2733.
Comments may also be submitted
electronically or through hand delivery/
courier by following the detailed
instructions in the ADDRESSES section of
the direct final rule located in the rules
section of this Federal Register.
FOR FURTHER INFORMATION CONTACT: Joe
Kordzi, Air Planning Section (6PD–L),
Environmental Protection Agency,
Region 6, 1445 Ross Avenue, Suite 700,
Dallas, Texas 75202–2733, telephone
(214) 665–7186; fax number 214–665–
7263; e-mail address
kordzi.joe@epa.gov.
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
In the
final rules section of this Federal
Register, EPA is approving the State’s
SIP submittal as a direct final rule
without prior proposal because the
Agency views this as a noncontroversial
submittal and anticipates no adverse
comments. A detailed rationale for the
approval is set forth in the direct final
rule. If no adverse comments are
received in response to this action rule,
no further activity is contemplated. If
EPA receives adverse comments, the
direct final rule will be withdrawn and
all public comments received will be
addressed in a subsequent final rule
based on this proposed rule. EPA will
not institute a second comment period.
Any parties interested in commenting
on this action should do so at this time.
Please note that if EPA receives adverse
comment on an amendment, paragraph,
or section of this rule and if that
provision may be severed from the
remainder of the rule, EPA may adopt
as final those provisions of the rule that
are not the subject of an adverse
comment.
For additional information, see the
direct final rule which is located in the
rules section of this Federal Register.
SUPPLEMENTARY INFORMATION:
Dated: March 16, 2009.
Lawrence E. Starfield,
Acting Regional Administrator, Region 6.
[FR Doc. E9–7297 Filed 3–31–09; 8:45 am]
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Alternative Intervals or Limits
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]]>Agencies
[Federal Register Volume 74, Number 61 (Wednesday, April 1, 2009)]
[Proposed Rules]
[Pages 14751-14759]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-7267]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0292; Directorate Identifier 2008-NM-011-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A310, and A300-600
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Airbus Model A300 and A310
series airplanes. The existing AD currently requires replacement of the
nose landing gear drag strut upper attachment pin. This proposed AD
would require revising the Airworthiness Limitations section (ALS)
[[Page 14752]]
of the Instructions for Continued Airworthiness (ICA) to require
additional life limits and/or replacements for certain main landing
gear and nose landing gear components, and would also expand the
applicability. This proposed AD results from revisions to the ALS of
the ICA to include new or more restrictive life limits and/or
replacements. We are proposing this AD to ensure the continued
structural integrity of these airplanes.
DATES: We must receive comments on this proposed AD by May 1, 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.
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 proposed 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. You may review copies of the referenced service
information 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.
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 proposed 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: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0292;
Directorate Identifier 2008-NM-011-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On July 21, 1987, we issued AD 87-16-06, amendment 39-5692 (52 FR
28241, July 29, 1987), for certain Airbus Model A300 and A310 series
airplanes. That AD requires replacement of the nose landing gear drag
strut upper attachment pin. That AD resulted from reports of pins which
were found to be improperly manufactured. We issued that AD to prevent
failure of the pin and collapse of the nose landing gear.
Actions Since Existing AD Was Issued
Since we issued AD 87-16-06, the manufacturer has revised the
Airworthiness Limitations Section (ALS) of the Instructions for
Continued Airworthiness (ICA) to include new or more restrictive life
limits and replacements for the main landing gear and the nose landing
gear. These new limits affect the replacement of the upper attachment
pin for the nose landing gear drag strut that was the subject of AD 87-
16-06.
In addition, European Aviation Safety Agency (EASA) Airworthiness
Directive 2007-0293, dated November 29, 2007, which is parallel to this
proposed AD, includes Model A300-600 series airplanes. Those airplane
models were not included in AD 87-16-06.
Relevant Service Information
Airbus has issued the following revisions to the ALS of the ICA.
These documents provide each mandatory replacement time, structural
inspection interval, and related structural inspection procedures or
other procedures (e.g., modifications).
For Model A300 Series Airplanes: ``Sub-part 1-2: Life
Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of Part 1,
``Safe Life Airworthiness Limitation Items,'' dated September 6, 2007.
For Model A300-600 Series Airplanes: ``Sub-part 1-2: Life
Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of Part 1,
``Safe Life Airworthiness Limitation Items,'' dated December 21, 2006.
For Model A310 Series Airplanes: ``Sub-part 1-2: Life
Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of Part 1,
``Safe Life Airworthiness Limitation Items,'' dated December 21, 2006.
Airbus has also issued Section 05-10-00, Revision 28, dated
February 27, 1998, of Chapter 5, ``Service Life Limits and Maintenance
Checks,'' of the A300 Aircraft Maintenance Manual. Section 05-10-00
includes life limit values for the nose and main landing gears. This
document is an alternate source for the life limits defined in Part 1,
``Safe Life Airworthiness Limitation Items,'' dated September 6, 2007,
of the ALS, for Model A300 series airplanes.
Airbus has also issued Service Information Letter (SIL) 32-118,
Revision 02, dated October 24, 2007. This SIL gives instructions for
calculating the life limit of main or nose landing gear parts where the
history of accumulated landings is partial or unknown, or where the
history of application details (airplane type, model, weight variant,
etc.) is partial or unknown.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. EASA mandated the
service information and issued Airworthiness Directive 2007-0292, dated
November 29, 2007, to ensure the continued airworthiness of these
airplanes in the European Union.
Other Relevant Rulemaking
On January 11, 1984, we issued AD 84-02-04 (49 FR 2746, January 23,
1984), for certain Airbus Model A300 B2 and B4 series airplanes. That
AD requires inspection of main landing gear hinge arms for corrosion
and cracks, and repair or modifications if needed. That AD also
requires replacement of the main landing gear shock absorber sliding
rod attachment fitting. That AD resulted from corrosion and cracks
found on these components. We issued that AD to prevent landing gear
failure.
The actions specified in paragraph (h) of this proposed AD would
satisfy the
[[Page 14753]]
requirements of paragraph A. of AD 84-02-04. There are no actions in
this proposed AD that would satisfy the requirements of paragraphs B.
and C. of AD 84-02-04.
FAA's Determination and Requirements of the Proposed 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.
This proposed AD would supersede AD 87-16-06 and would retain the
requirements of that existing AD. This proposed AD would also add
airplanes to the applicability and require revising the ALS of the ICA
to incorporate additional life limits and/or structural inspections for
certain main landing gear and nose landing gear components.
Change to Existing AD
This proposed AD would retain the requirements of AD 87-16-06.
Since AD 87-16-06 was issued, the AD format has been revised. As a
result, the corresponding paragraph identifiers have changed in this
proposed AD, and paragraph (g) of this proposed AD corresponds to
paragraph A. of AD 87-16-06.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Replacement (required by AD 87-16-06)................... 7 $80 $3,300 $3,860 94 $362,840
Revision (new proposed action).......................... 1 80 0 80 238 19,040
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
Reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-5692 (52 FR 28241, July 29, 1987) and adding the
following new airworthiness directive (AD):
Airbus: Docket No. FAA-2009-0292; Directorate Identifier 2008-NM-
011-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by May 1,
2009.
Affected ADs
(b) This AD supersedes AD 87-16-06.
Applicability
(c) This AD applies to all Airbus Model A300, A310, and A300-600
series airplanes, certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
Gear.
Unsafe Condition
(e) This AD results from revisions to the Airworthiness
Limitations section (ALS) of the Instructions for Continued
Airworthiness (ICA) to include new or more restrictive life limits
and/or replacements. We are issuing this AD to ensure the continued
structural integrity of these airplanes.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new replacements. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these replacements, the operator may not be able
to accomplish the replacements described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (l) of this AD. The request should include a
description of changes to the required replacements that will ensure
the continued operational safety of the airplane.
[[Page 14754]]
Restatement of the Requirements of AD 87-16-06
(g) For Model A300 and A310 Series Airplanes: Prior to the
accumulation of 16,000 landings, or within the next 2,000 landings
after September 3, 1987 (the effective date of AD 87-16-06),
whichever occurs later, replace the nose landing gear drag strut
upper attachment pin in accordance with Airbus Service Bulletin
A300-32-374, Revision 1, dated July 15, 1986 (applicable to Model
A300 airplanes); or A310-32-2023, Revision 2, dated November 14,
1986 (applicable to Model A310 airplanes).
New Requirements of This AD
ALS Revision
(h) For Model A300, A310, and A300-600 Series Airplanes: Within
3 months after the effective date of this AD, revise the ALS of the
ICA to incorporate the applicable document listed in paragraph
(h)(1), (h)(2), or (h)(3) of this AD. Accomplishing the actions
specified in the applicable document satisfies the requirements of
paragraph A. of AD 84-02-04, amendment 39-4795.
(1) For Model A300 Series Airplanes: Incorporate the document
listed in paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
(i) Section 05-10-00, Revision 28, dated February 27, 1998, of
Chapter 5, ``Service Life Limits and Maintenance Checks,'' of the
Airbus A300 Aircraft Maintenance Manual, except that the parts
listed in Table 1 of this AD are subject to the life limits defined
in the document listed in paragraph (h)(1)(ii) of this AD.
(ii) ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3:
Demonstrated fatigue lives'' of Part 1, ``Safe Life Airworthiness
Limitation Items,'' dated September 6, 2007, of the Airbus A300 ALS.
Table 1--Parts Subject to the Life Limits Specified in the Document
Identified in Paragraph (h)(1)(ii) of This AD
------------------------------------------------------------------------
Part Number (P/N) Part name
------------------------------------------------------------------------
P/N C61643-2, P/N C61643-4, P/N C61643- Main landing gear (MLG) shock
5. absorber end fitting.
P/N A32210001205xx..................... Nose landing gear (NLG) pintle
pin.
P/N C62037-1........................... NLG shock absorber bottom.
P/N 196-0328-501....................... Cross beam (Pratt & Whitney
forward engine mount).
------------------------------------------------------------------------
(2) For Model A310 Series Airplanes: Incorporate ``Sub-part 1-2:
Life Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of
Part 1, ``Safe Life Airworthiness Limitation Items,'' dated December
21, 2006, of the Airbus A310 ALS.
(3) For Model A300-600 Series Airplanes: Incorporate ``Sub-part
1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives''
of Part 1, ``Safe Life Airworthiness Limitation Items,'' dated
December 21, 2006, of the Airbus A300-600 ALS.
Initial Compliance Times and Repetitive Inspections
(i) Do the replacement at the applicable time specified in
paragraph (i)(1) or (i)(2) of this AD, except as provided by
paragraph (j) of this AD. The replacement must be done thereafter
within the interval specified in the applicable document identified
in paragraph (h)(1), (h)(2), or (h)(3) of this AD.
(1) For any life limitation/task that has been complied with
before the effective date of this AD in accordance with the
applicable document listed in paragraph (h)(1), (h)(2), or (h)(3) of
this AD, or in accordance with paragraph (g) of this AD, use the
last accomplishment of each limitation/task as a starting point for
accomplishing each corresponding limitation/task required by this
AD.
(2) For any life limitation/task that has not been complied with
before the effective date of this AD in accordance with the
applicable document listed in paragraphs (h)(1), (h)(2), and (h)(3)
of this AD, or in accordance with paragraph (g) of this AD, the
initial compliance time starts from the date of initial entry into
service as defined in the applicable document.
Special Compliance Times
(j) For any airplane on which the history of accumulated
landings is partial or unknown, or where the history of application
details (airplane type, model, weight variant, etc.) is partial or
unknown, with or without using the information in Airbus Service
Information Letter 32-118, Revision 02, dated October 24, 2007:
Parts listed in Figure 1 of this AD must be replaced at the
associated compliance time. The replacement must be done thereafter
at the interval specified in the applicable document(s) specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this AD.
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Alternative Intervals or Limits
(k) Except as provided by paragraph (l) of this AD, after
accomplishing the actions specified in paragraphs (h), (i), and (j)
of this AD, no alternative replacements, replacement intervals, or
limitations may be used.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, Manager, ANM-116, International Branch,
Transport Airplane Directorate, 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: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-1622; fax (425) 227-1149.
(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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
Related Information
(m) European Aviation Safety Agency (EASA) Airworthiness
Directive 2007-0293, dated November 29, 2007, also addresses the
subject of this AD.
Issued in Renton, Washington, on March 12, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-7267 Filed 3-31-09; 8:45 am]
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