Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A300 and A310 Series Airplanes, 60611-60614 [2010-24257]
Download as PDF
<![CDATA[
Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Rules and Regulations
dated January 12, 2010; for related
information.
ACTION:
Material Incorporated by Reference
(m) You must use Bombardier Service
Bulletin 670BA–27–051, dated May 14, 2009;
and Bombardier Service Bulletin 670BA–27–
053, Revision B, dated January 12, 2010; as
applicable; to do the actions required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Bombardier Service Bulletin 670BA–27–053,
Revision B, dated January 12, 2010, under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Bombardier Service Bulletin
670BA–27–051, dated May 14, 2009, on
November 13, 2009 (74 FR 55767, October
29, 2009).
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(4) You may review copies of the 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.
(5) You may also review copies of the
service information that is incorporated by
reference 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.
Issued in Renton, Washington on
September 16, 2010.
Robert D. Breneman,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–24255 Filed 9–30–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0478; Directorate
Identifier 2008–NM–090–AD; Amendment
39–16451; AD 2010–20–16]
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
*
*
*
*
*
SUMMARY:
Two cases of complete nose landing gear
(NLG) shock absorber bolts failure were
reported to the manufacturer. In both cases,
the crew was unable to retract the gear and
was forced to an In Flight Turn Back. In one
case, the aircraft experienced a low speed
runway excursion. The root cause of the bolts
failure has been identified being due to a
bolt(s) over-torque. The investigation has
highlighted that the design of the NLG shock
absorber was not tolerant to the over-torque,
and an inspection plan has been developed
to track any NLG shock absorber-to-main
barrel attachment bolts status. * * *
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
November 5, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 5, 2010.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: 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.
SUPPLEMENTARY INFORMATION:
Discussion
Airworthiness Directives; Airbus Model
A300 B4–600, B4–600R, and F4–600R
Series Airplanes, and Model A300 C4–
605R Variant F Airplanes (Collectively
Called A300–600 Series Airplanes);
and Model A300 and A310 Series
Airplanes
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on May 19, 2010 (75 FR 27956).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
*
*
*
*
*
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
Two cases of complete nose landing gear
(NLG) shock absorber bolts failure were
reported to the manufacturer. In both cases,
the crew was unable to retract the gear and
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Final rule.
AGENCY:
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Jkt 223001
PO 00000
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Fmt 4700
Sfmt 4700
60611
was forced to an In Flight Turn Back. In one
case, the aircraft experienced a low speed
runway excursion. The root cause of the bolts
failure has been identified being due to a
bolt(s) over-torque. The investigation has
highlighted that the design of the NLG shock
absorber was not tolerant to the over-torque,
and an inspection plan has been developed
to track any NLG shock absorber-to-main
barrel attachment bolts status. The
preliminary inspection plan, required by
DGAC France Airworthiness Directive (AD)
F–2004–075 and F–2004–076, has allowed
limiting the number of findings: High at the
initial inspection, it has decreased following
the repetitive inspections.
This new [European Aviation Safety
Agency (EASA)] AD retains the requirements
of those ADs, which are superseded, and
requires a repetitive torque check of the NLG
shock absorber-to-main barrel attachment
bolts with new thresholds and intervals. This
new AD also refers to an optional
modification as terminating action.
*
*
*
*
*
The optional modification involves
modifying the shock absorber-to-barrel
attachment to increase over-torque
tolerances. The actions to address the
unsafe condition also include inspecting
the NLG shock absorber-to-main barrel
attachment bolts and doing corrective
actions. The corrective actions include
replacing bolts, screws, nuts, washers,
and cotter pins; contacting Airbus for
repair and doing the repair; and
modifying the shock absorber; as
applicable. The inspection of the NLG
shock absorber-to-main barrel
attachment bolts is repeated at intervals
not to exceed 400 flight hours or 1,000
flight cycles, depending on the
inspection results and corrective actions
performed. You may obtain further
information by examining the MCAI in
the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Request To Remove Reporting
Requirement
UPS requests that we remove the
requirement to submit a report after
each inspection that results in re-torque
or replacement of bolts. UPS contends
that Airbus has had sufficient time to
gather enough data to determine the root
cause of the over-torqued bolts. UPS has
done the inspections of the NLG in
accordance with Airbus All Operator
Telex A300–32A6093, dated April 22,
2004, since it was published. UPS states
that Airbus has been collecting data
from airlines that operate under EASA
regulations. UPS also points out that,
although it has been doing the
inspections for 6 years, it would need to
do an additional inspection within 30
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Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Rules and Regulations
days to document the findings and
complete the inspection report. UPS
believes this reporting requirement
places an unnecessary burden on the
operator.
We agree with the request for the
reasons stated above. Airbus no longer
needs this information from operators.
We have removed paragraph (k) of the
NPRM and have re-identified
subsequent paragraphs in this AD
accordingly.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
We determined that this change will not
increase the economic burden on any
operator or increase the scope of the AD.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a Note within the AD.
mstockstill on DSKH9S0YB1PROD with RULES
Costs of Compliance
We estimate that this AD will affect
229 products of U.S. registry. We also
estimate that it will take about 2 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $38,930, or $170 per product.
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
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16:31 Sep 30, 2010
Jkt 223001
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 determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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: 49 U.S.C. 106(g), 40113, 44701.
PO 00000
Frm 00040
Fmt 4700
Sfmt 4700
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2010–20–16 Airbus: Amendment 39–
16451. Docket No. FAA–2010–0478;
Directorate Identifier 2008–NM–090–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective November 5, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300
B2–1A, B2–1C, B4–2C, B2K–3C, B4–103, B2–
203, and B4–203 airplanes; Model A300 B4–
601, B4–603, B4–620, B4–622, B4–605R, B4–
622R, F4–605R, F4–622R, and C4–605R
Variant F airplanes; and Model A310–203,
–204, –221, –222, –304, –322, –324, and –325
airplanes; all certified models, all serial
numbers, certificated in any category; except
airplanes on which Airbus Modification
13212 has been done in production or Airbus
Service Bulletin A300–32–0453, A310–32–
2135, or A300–32–6099 has been done in
service.
Subject
(d) Air Transport Association (ATA) of
America Code 32: Landing gear.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Two cases of complete nose landing gear
(NLG) shock absorber bolts failure were
reported to the manufacturer. In both cases,
the crew was unable to retract the gear and
was forced to an In Flight Turn Back. In one
case, the aircraft experienced a low speed
runway excursion. The root cause of the bolts
failure has been identified being due to a
bolt(s) over-torque. The investigation has
highlighted that the design of the NLG shock
absorber was not tolerant to the over-torque,
and an inspection plan has been developed
to track any NLG shock absorber-to-main
barrel attachment bolts status. The
preliminary inspection plan, required by
DGAC France Airworthiness Directive (AD)
F–2004–075 and F–2004–076, has allowed
limiting the number of findings: High at the
initial inspection, it has decreased following
the repetitive inspections.
This new [European Aviation Safety
Agency (EASA)] AD retains the requirements
of those ADs, which are superseded, and
requires a repetitive torque check of the NLG
shock absorber-to-main barrel attachment
bolts with new thresholds and intervals. This
new AD also refers to an optional
modification as terminating action.
*
*
*
*
*
The optional modification involves
modifying the shock absorber-to-barrel
attachment to increase over-torque
tolerances. The actions to address the unsafe
condition also include inspecting the NLG
shock absorber-to-main barrel attachment
bolts and corrective actions. The corrective
actions include replacing bolts, screws, nuts,
washers, and cotter pins; contacting Airbus
E:\FR\FM\01OCR1.SGM
01OCR1
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Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Rules and Regulations
for repair and doing the repair; and
modifying the shock absorber; as applicable.
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.
Inspection and Corrective Action
(g) At the applicable time specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD:
Do a visual inspection to detect operational
condition (i.e., free of corrosion and not
deformed) and inspect rotation/torque of the
NLG shock absorber-to-main barrel
attachment bolts and do all applicable
corrective actions, in accordance with the
applicable Airbus all operators telex (AOT)
identified in Table 1 of this AD. Do all
applicable corrective actions before further
flight. Thereafter, repeat the inspection at the
applicable intervals, depending on
inspection results and the corrective actions
performed, as specified in the applicable
Airbus AOT identified in Table 1 of this AD.
(1) For airplanes on which the NLG has
been overhauled (the bolts have been
removed) as of the effective date of this AD:
Within 30 days or 1,000 flight cycles on the
NLG after the effective date of this AD,
whichever occurs later.
(2) For airplanes on which, as of the
effective date of this AD, the NLG has
accumulated less than 1,000 total flight
cycles, and has not been overhauled (the
bolts have never been removed), since
manufacture of the NLG: Before the
accumulation of 1,000 total flight cycles on
the NLG, or within 30 days after the effective
date of this AD, whichever occurs later.
(3) For airplanes on which, as of the
effective date of this AD, the NLG has
accumulated 1,000 or more total flight cycles,
and has not been overhauled since new (the
bolts have never been removed): Within 30
days after the effective date of this AD.
TABLE 1—AIRBUS ALL OPERATOR TELEXES
For model—
Use airbus all operator telex—
Dated—
A300 series airplanes .................................................................................
A300 B4–600, B4–600R, and F4–600R Series Airplanes, and Model
A300 C4-605R Variant F airplanes (Collectively called A300–600 series airplanes).
A310 series airplanes .................................................................................
A300–32A0447 ........................................................
A300–32A6093 ........................................................
April 22, 2004.
April 22, 2004.
A310–32A2132 ........................................................
April 22, 2004.
Torque Load Inspection and Corrective
Action
(h) At the latest of the compliance times
specified in paragraphs (h)(1), (h)(2), and
(h)(3) of this AD, do an inspection of the
torque load of the nuts of the NLG shock
absorber-to-main barrel attachment bolts in
accordance with the Accomplishment
Instructions of the applicable Airbus service
bulletin listed in Table 2 of this AD.
Depending on the torque load value found
during the inspection, before further flight:
Retighten the bolt(s) or replace the discrepant
bolt(s), or replace all bolts, in accordance
with the applicable Airbus service bulletin
listed in Table 2 of this AD. Thereafter,
repeat the torque load inspection at intervals
not to exceed 3,200 flight cycles or 30
months time-in-service accumulated by the
NLG, whichever occurs first.
(1) Within 3,200 flight cycles or 30 months
since NLG’s first flight, whichever occurs
first.
(2) Within 3,200 flight cycles or 30 months
accumulated by the NLG since installation of
new bolts, whichever occurs first.
(3) Within 3,200 flight cycles or 30 months
after the effective date of this AD, whichever
occurs first.
TABLE 2—SERVICE INFORMATION FOR INSPECTIONS
Use airbus
mandatory service
bulletin—
For model—
A300 series airplanes ...................................................................................................................
A300–600 series airplanes ...........................................................................................................
A310 series airplanes ...................................................................................................................
(i) After accomplishment of the initial
inspection in accordance with paragraph (h)
of this AD, as applicable, the repetitive
inspections of paragraph (g) of this AD are no
longer required.
Optional Terminating Action
(j) For airplanes on which the modification
of the shock absorber-to-barrel attachment
has been done in accordance with the
Revision
level—
A300–32–0447
A300–32–6093
A310–32–2132
01
01
01
Dated—
June 1, 2007.
June 1, 2007.
June 1, 2007.
applicable service bulletin listed in Table 3
of this AD, the requirements of this AD are
no longer required, as long as that
modification remains installed.
TABLE 3—SERVICE INFORMATION FOR OPTIONAL TERMINATING ACTION
Use
airbus service
bulletin—
For model—
mstockstill on DSKH9S0YB1PROD with RULES
A300 series airplanes ...........................................................................................................................................
A300–600 series airplanes ...................................................................................................................................
A310 series airplanes ...........................................................................................................................................
FAA AD Differences
Other FAA AD Provisions
Note 1: This AD differs from the MCAI
and/or service information as follows: No
Differences.
(k) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
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A300–32–0453
A300–32–6099
A310–32–2135
Dated—
June 1, 2007.
June 1, 2007.
June 1, 2007.
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)
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227–2125; fax (425) 227–1149. 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.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(l) Refer to MCAI EASA Airworthiness
Directive 2008–0052R1, dated June 30, 2008;
and the service information identified in
Tables 1, 2, and 3 of this AD; for related
information.
Material Incorporated by Reference
(m) You must use the applicable service
information contained in Table 4 of this AD
to do the actions required by this AD, unless
the AD specifies otherwise. If you
accomplish the optional terminating actions
specified by this AD, you must use the
applicable service information identified in
Table 5 of this AD to perform those actions,
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 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.airwortheas@airbus.com; Internet: https://
www.airbus.com.
(3) You may review copies of the 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.
(4) You may also review copies of the
service information that is incorporated by
reference 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 4—MATERIAL INCORPORATED BY REFERENCE FOR ACTIONS REQUIRED IN THIS AD
Document
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Revision
All Operator Telex A300-32A0447 ...........................................................................
All Operator Telex A300-32A6093 ...........................................................................
All Operator Telex A310-32A2132 ...........................................................................
Mandatory Service Bulletin A300–32–0447, excluding Appendix 01 ......................
Mandatory Service Bulletin A300–32–6093, excluding Appendix 01 ......................
Mandatory Service Bulletin A310–32–2132, excluding Appendix 01 ......................
Original ...........................................
Original ...........................................
Original ...........................................
01 ...................................................
01 ...................................................
01 ...................................................
TABLE 5—MATERIAL INCORPORATED ACTION: Final rule.
BY REFERENCE FOR THE OPTIONAL
SUMMARY: We are adopting a new
TERMINATING ACTION IN THIS AD
airworthiness directive (AD) for Model
Airbus service
bulletin—
Dated—
A300–32–0453 ......................
A300–32–6099 ......................
A310–32–2135 ......................
June 1, 2007.
June 1, 2007.
June 1, 2007.
Issued in Renton, Washington, on
September 16, 2010.
Robert D. Breneman,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–24257 Filed 9–30–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
mstockstill on DSKH9S0YB1PROD with RULES
[Docket No. FAA–2010–0035; Directorate
Identifier 2009–NM–066–AD; Amendment
39–16447; AD 2010–20–12]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747–400, 747–400D,
and 747–400F Series Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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16:31 Sep 30, 2010
Jkt 223001
747–400, 747–400D, and 747–400F
series airplanes. This AD requires
installing a hot short protector (HSP) for
the fuel quantity indicating system
(FQIS) of the center fuel tank and, for
certain airplanes, the horizontal
stabilizer fuel tank. This AD results
from fuel system reviews conducted by
the manufacturer. We are issuing this
AD to prevent an electrical hot short
from a source outside the FQIS to the
densitometer wiring from causing
failure of the FQIS densitometer
resistors, which could result in an
ignition source inside the center or
horizontal stabilizer fuel tanks. An
ignition source, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane. This AD is effective
November 5, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of November 5, 2010.
ADDRESSES: 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
PO 00000
Frm 00042
Fmt 4700
Sfmt 4700
Date
April 22, 2004.
April 22, 2004.
April 22, 2004.
June 1, 2007.
June 1, 2007.
June 1, 2007.
me.boecom@boeing.com; Internet
https://www.myboeingfleet.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:
Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6482; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to
certain Model 747–400, 747–400D, and
747–400F series airplanes. That NPRM
E:\FR\FM\01OCR1.SGM
01OCR1
]]>Agencies
[Federal Register Volume 75, Number 190 (Friday, October 1, 2010)]
[Rules and Regulations]
[Pages 60611-60614]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-24257]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0478; Directorate Identifier 2008-NM-090-AD;
Amendment 39-16451; AD 2010-20-16]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and
F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes
(Collectively Called A300-600 Series Airplanes); and Model A300 and
A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
* * * * *
Two cases of complete nose landing gear (NLG) shock absorber
bolts failure were reported to the manufacturer. In both cases, the
crew was unable to retract the gear and was forced to an In Flight
Turn Back. In one case, the aircraft experienced a low speed runway
excursion. The root cause of the bolts failure has been identified
being due to a bolt(s) over-torque. The investigation has
highlighted that the design of the NLG shock absorber was not
tolerant to the over-torque, and an inspection plan has been
developed to track any NLG shock absorber-to-main barrel attachment
bolts status. * * *
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective November 5, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 5,
2010.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: 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.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on May 19, 2010 (75 FR
27956). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
* * * * *
Two cases of complete nose landing gear (NLG) shock absorber
bolts failure were reported to the manufacturer. In both cases, the
crew was unable to retract the gear and was forced to an In Flight
Turn Back. In one case, the aircraft experienced a low speed runway
excursion. The root cause of the bolts failure has been identified
being due to a bolt(s) over-torque. The investigation has
highlighted that the design of the NLG shock absorber was not
tolerant to the over-torque, and an inspection plan has been
developed to track any NLG shock absorber-to-main barrel attachment
bolts status. The preliminary inspection plan, required by DGAC
France Airworthiness Directive (AD) F-2004-075 and F-2004-076, has
allowed limiting the number of findings: High at the initial
inspection, it has decreased following the repetitive inspections.
This new [European Aviation Safety Agency (EASA)] AD retains the
requirements of those ADs, which are superseded, and requires a
repetitive torque check of the NLG shock absorber-to-main barrel
attachment bolts with new thresholds and intervals. This new AD also
refers to an optional modification as terminating action.
* * * * *
The optional modification involves modifying the shock absorber-to-
barrel attachment to increase over-torque tolerances. The actions to
address the unsafe condition also include inspecting the NLG shock
absorber-to-main barrel attachment bolts and doing corrective actions.
The corrective actions include replacing bolts, screws, nuts, washers,
and cotter pins; contacting Airbus for repair and doing the repair; and
modifying the shock absorber; as applicable. The inspection of the NLG
shock absorber-to-main barrel attachment bolts is repeated at intervals
not to exceed 400 flight hours or 1,000 flight cycles, depending on the
inspection results and corrective actions performed. You may obtain
further information by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received.
Request To Remove Reporting Requirement
UPS requests that we remove the requirement to submit a report
after each inspection that results in re-torque or replacement of
bolts. UPS contends that Airbus has had sufficient time to gather
enough data to determine the root cause of the over-torqued bolts. UPS
has done the inspections of the NLG in accordance with Airbus All
Operator Telex A300-32A6093, dated April 22, 2004, since it was
published. UPS states that Airbus has been collecting data from
airlines that operate under EASA regulations. UPS also points out that,
although it has been doing the inspections for 6 years, it would need
to do an additional inspection within 30
[[Page 60612]]
days to document the findings and complete the inspection report. UPS
believes this reporting requirement places an unnecessary burden on the
operator.
We agree with the request for the reasons stated above. Airbus no
longer needs this information from operators. We have removed paragraph
(k) of the NPRM and have re-identified subsequent paragraphs in this AD
accordingly.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the change described previously. We determined that this change
will not increase the economic burden on any operator or increase the
scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a Note within the AD.
Costs of Compliance
We estimate that this AD will affect 229 products of U.S. registry.
We also estimate that it will take about 2 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $38,930, or $170 per product.
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 determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
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 adding the following new AD:
2010-20-16 Airbus: Amendment 39-16451. Docket No. FAA-2010-0478;
Directorate Identifier 2008-NM-090-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
5, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 B2-1A, B2-1C, B4-2C,
B2K-3C, B4-103, B2-203, and B4-203 airplanes; Model A300 B4-601, B4-
603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R
Variant F airplanes; and Model A310-203, -204, -221, -222, -304, -
322, -324, and -325 airplanes; all certified models, all serial
numbers, certificated in any category; except airplanes on which
Airbus Modification 13212 has been done in production or Airbus
Service Bulletin A300-32-0453, A310-32-2135, or A300-32-6099 has
been done in service.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
gear.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Two cases of complete nose landing gear (NLG) shock absorber
bolts failure were reported to the manufacturer. In both cases, the
crew was unable to retract the gear and was forced to an In Flight
Turn Back. In one case, the aircraft experienced a low speed runway
excursion. The root cause of the bolts failure has been identified
being due to a bolt(s) over-torque. The investigation has
highlighted that the design of the NLG shock absorber was not
tolerant to the over-torque, and an inspection plan has been
developed to track any NLG shock absorber-to-main barrel attachment
bolts status. The preliminary inspection plan, required by DGAC
France Airworthiness Directive (AD) F-2004-075 and F-2004-076, has
allowed limiting the number of findings: High at the initial
inspection, it has decreased following the repetitive inspections.
This new [European Aviation Safety Agency (EASA)] AD retains the
requirements of those ADs, which are superseded, and requires a
repetitive torque check of the NLG shock absorber-to-main barrel
attachment bolts with new thresholds and intervals. This new AD also
refers to an optional modification as terminating action.
* * * * *
The optional modification involves modifying the shock absorber-to-
barrel attachment to increase over-torque tolerances. The actions to
address the unsafe condition also include inspecting the NLG shock
absorber-to-main barrel attachment bolts and corrective actions. The
corrective actions include replacing bolts, screws, nuts, washers,
and cotter pins; contacting Airbus
[[Page 60613]]
for repair and doing the repair; and modifying the shock absorber;
as applicable.
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.
Inspection and Corrective Action
(g) At the applicable time specified in paragraph (g)(1),
(g)(2), or (g)(3) of this AD: Do a visual inspection to detect
operational condition (i.e., free of corrosion and not deformed) and
inspect rotation/torque of the NLG shock absorber-to-main barrel
attachment bolts and do all applicable corrective actions, in
accordance with the applicable Airbus all operators telex (AOT)
identified in Table 1 of this AD. Do all applicable corrective
actions before further flight. Thereafter, repeat the inspection at
the applicable intervals, depending on inspection results and the
corrective actions performed, as specified in the applicable Airbus
AOT identified in Table 1 of this AD.
(1) For airplanes on which the NLG has been overhauled (the
bolts have been removed) as of the effective date of this AD: Within
30 days or 1,000 flight cycles on the NLG after the effective date
of this AD, whichever occurs later.
(2) For airplanes on which, as of the effective date of this AD,
the NLG has accumulated less than 1,000 total flight cycles, and has
not been overhauled (the bolts have never been removed), since
manufacture of the NLG: Before the accumulation of 1,000 total
flight cycles on the NLG, or within 30 days after the effective date
of this AD, whichever occurs later.
(3) For airplanes on which, as of the effective date of this AD,
the NLG has accumulated 1,000 or more total flight cycles, and has
not been overhauled since new (the bolts have never been removed):
Within 30 days after the effective date of this AD.
Table 1--Airbus All Operator Telexes
------------------------------------------------------------------------
Use airbus all
For model-- operator telex-- Dated--
------------------------------------------------------------------------
A300 series airplanes......... A300-32A0447..... April 22, 2004.
A300 B4-600, B4-600R, and F4- A300-32A6093..... April 22, 2004.
600R Series Airplanes, and
Model A300 C4[dash]605R
Variant F airplanes
(Collectively called A300-600
series airplanes).
A310 series airplanes......... A310-32A2132..... April 22, 2004.
------------------------------------------------------------------------
Torque Load Inspection and Corrective Action
(h) At the latest of the compliance times specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this AD, do an inspection
of the torque load of the nuts of the NLG shock absorber-to-main
barrel attachment bolts in accordance with the Accomplishment
Instructions of the applicable Airbus service bulletin listed in
Table 2 of this AD. Depending on the torque load value found during
the inspection, before further flight: Retighten the bolt(s) or
replace the discrepant bolt(s), or replace all bolts, in accordance
with the applicable Airbus service bulletin listed in Table 2 of
this AD. Thereafter, repeat the torque load inspection at intervals
not to exceed 3,200 flight cycles or 30 months time-in-service
accumulated by the NLG, whichever occurs first.
(1) Within 3,200 flight cycles or 30 months since NLG's first
flight, whichever occurs first.
(2) Within 3,200 flight cycles or 30 months accumulated by the
NLG since installation of new bolts, whichever occurs first.
(3) Within 3,200 flight cycles or 30 months after the effective
date of this AD, whichever occurs first.
Table 2--Service Information for Inspections
----------------------------------------------------------------------------------------------------------------
Use airbus
For model-- mandatory service Revision Dated--
bulletin-- level--
----------------------------------------------------------------------------------------------------------------
A300 series airplanes........................ A300-32-0447 01 June 1, 2007.
A300-600 series airplanes.................... A300-32-6093 01 June 1, 2007.
A310 series airplanes........................ A310-32-2132 01 June 1, 2007.
----------------------------------------------------------------------------------------------------------------
(i) After accomplishment of the initial inspection in
accordance with paragraph (h) of this AD, as applicable, the
repetitive inspections of paragraph (g) of this AD are no longer
required.
Optional Terminating Action
(j) For airplanes on which the modification of the shock
absorber-to-barrel attachment has been done in accordance with the
applicable service bulletin listed in Table 3 of this AD, the
requirements of this AD are no longer required, as long as that
modification remains installed.
Table 3--Service Information for Optional Terminating Action
------------------------------------------------------------------------
Use airbus
For model-- service Dated--
bulletin--
------------------------------------------------------------------------
A300 series airplanes........... A300-32-0453 June 1, 2007.
A300-600 series airplanes....... A300-32-6099 June 1, 2007.
A310 series airplanes........... A310-32-2135 June 1, 2007.
------------------------------------------------------------------------
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No Differences.
Other FAA AD Provisions
(k) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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: Dan
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425)
[[Page 60614]]
227-2125; fax (425) 227-1149. 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.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(l) Refer to MCAI EASA Airworthiness Directive 2008-0052R1,
dated June 30, 2008; and the service information identified in
Tables 1, 2, and 3 of this AD; for related information.
Material Incorporated by Reference
(m) You must use the applicable service information contained in
Table 4 of this AD to do the actions required by this AD, unless the
AD specifies otherwise. If you accomplish the optional terminating
actions specified by this AD, you must use the applicable service
information identified in Table 5 of this AD to perform those
actions, 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
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.
(3) You may review copies of the 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.
(4) You may also review copies of the service information that
is incorporated by reference 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 4--Material Incorporated by Reference for Actions Required in This
AD
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Airbus All Operator Telex Original......... April 22, 2004.
A300[dash]32A0447.
Airbus All Operator Telex Original......... April 22, 2004.
A300[dash]32A6093.
Airbus All Operator Telex Original......... April 22, 2004.
A310[dash]32A2132.
Airbus Mandatory Service 01............... June 1, 2007.
Bulletin A300-32-0447,
excluding Appendix 01.
Airbus Mandatory Service 01............... June 1, 2007.
Bulletin A300-32-6093,
excluding Appendix 01.
Airbus Mandatory Service 01............... June 1, 2007.
Bulletin A310-32-2132,
excluding Appendix 01.
------------------------------------------------------------------------
Table 5--Material Incorporated by Reference for the Optional Terminating
Action in This AD
------------------------------------------------------------------------
Airbus service bulletin-- Dated--
------------------------------------------------------------------------
A300-32-0453............................. June 1, 2007.
A300-32-6099............................. June 1, 2007.
A310-32-2135............................. June 1, 2007.
------------------------------------------------------------------------
Issued in Renton, Washington, on September 16, 2010.
Robert D. Breneman,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-24257 Filed 9-30-10; 8:45 am]
BILLING CODE 4910-13-P
