Airworthiness Directives; Airbus Model A310 Airplanes, 18722-18725 [E8-7163]
Download as PDF
<![CDATA[
18722
Federal Register / Vol. 73, No. 67 / Monday, April 7, 2008 / Proposed Rules
identified, we might consider further
rulemaking then.
Costs of Compliance
There are about 1,064 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Work hours
Average labor
rate per hour
Parts
Cost per
airplane
Number of
U.S.-registered
airplanes
Fleet cost
AFM revision ............................................
1
$80
$0
$80
340
$27,200
Authority for this Rulemaking
List of Subjects in 14 CFR Part 39
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.
Air transportation, Aircraft, Aviation
safety, Safety.
rfrederick on PROD1PC67 with PROPOSALS
Regulatory Findings
15:07 Apr 04, 2008
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.
Affected ADs
(b) None.
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Applicability
(c) This AD applies to Boeing Model 747
airplanes and Model 767 airplanes, certified
in any category, equipped with General
Electric CF6–80C2 or CF6–80A series
engines.
Issued in Renton, Washington, on March
27, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–7153 Filed 4–4–08; 8:45 am]
Unsafe Condition
(d) This AD results from reports of several
in-flight engine flameouts, including
multiple dual engine flameout events and
one total power loss event, in ice-crystal
icing conditions. We are issuing this AD to
ensure that the flightcrew has the proper
procedures to follow in certain icing
conditions. These certain icing conditions
could cause a multiple engine flameout
during flight without the ability of the
engines to be relit, and consequent forced
landing of the airplane.
BILLING CODE 4910–13–P
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Airworthiness Directives; Airbus Model
A310 Airplanes
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2008–0402;
Directorate Identifier 2007–NM–165–AD.
Comments Due Date
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.
VerDate Aug<31>2005
The Proposed Amendment
Jkt 214001
Airplane Flight Manual (AFM) Revision
(f) Within 14 days after the effective date
of this AD, revise the Limitations Section of
the Boeing 747 or 767 AFM, as applicable, to
include the following statement. This may be
done by inserting a copy of this AD into the
AFM.
‘‘Prior to descent in visible moisture and
TAT less than 10 °C, including SAT less than
¥40 °C, nacelle anti-ice switch must be in
the ON position.’’
Note 1: When a statement identical to that
in paragraph (f) of this AD has been included
in the general revisions of the AFM, the
general revisions may be inserted into the
AFM, and the copy of this AD may be
removed from the AFM.
(a) The FAA must receive comments on
this AD action by May 22, 2008.
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0406; Directorate
Identifier 2007–NM–196–AD]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
AGENCY:
E:\FR\FM\07APP1.SGM
07APP1
Federal Register / Vol. 73, No. 67 / Monday, April 7, 2008 / Proposed Rules
Notice of proposed rulemaking
(NPRM).
ACTION:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above that would
supersede an existing AD. This
proposed 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:
During routine visual inspection, a crack
has been found in the wing MLG (main
landing gear) rib 5 forward attachment lug on
two A310 in-service aircraft. Laboratory
examination of one of the cracked ribs
confirmed that the crack is due to the
presence of pitting corrosion in the forward
lug holes. Also on both aircraft medium to
heavy corrosion was found in the forward
lugs on the opposite wing after removal of
the bushes. This situation if not detected,
could affect the structural integrity of the
MLG attachment.
*
*
*
*
*
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by May 7, 2008.
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 W12–40, 1200 New Jersey
Avenue, SE., Washington, DC, between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
rfrederick on PROD1PC67 with PROPOSALS
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 this proposed AD, 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.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
VerDate Aug<31>2005
15:07 Apr 04, 2008
Jkt 214001
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–2008–0406; Directorate Identifier
2007–NM–196–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 based on 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 December 7, 2006, we issued AD
2007–02–09, Amendment 39–14896 (72
FR 2612, January 22, 2007). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2007–02–09, the
type certificate holder has developed a
new inspection using ultrasonic
techniques. We have determined that
the existing AD must be superseded to
add repair or replacement of cracked
main landing gear (MLG) Rib 5, provide
the new inspection as an option, and
reduce the applicability of the AD to
exclude airplanes on which Airbus
Service Bulletin A310–57–2090 has
been done.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2007–0195,
dated July 19, 2007 (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
During routine visual inspection, a crack
has been found in the wing MLG (main
landing gear) rib 5 forward attachment lug on
two A310 in-service aircraft. Laboratory
examination of one of the cracked ribs
confirmed that the crack is due to the
presence of pitting corrosion in the forward
lug holes. Also on both aircraft medium to
heavy corrosion was found in the forward
lugs on the opposite wing after removal of
the bushes. This situation if not detected,
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
18723
could affect the structural integrity of the
MLG attachment. As an interim measure,
Airbus published Alert Service Bulletin
(ASB) A310–57A2088 to introduce a
repetitive detailed visual inspection (DVI) of
the forward attachment lug of MLG Rib 5.
EASA issued Emergency Airworthiness
Directive (EAD) 2006–0335–E [which
corresponds to FAA AD 2007–02–09] to
require the accomplishment of this repetitive
DVI.
In order to ensure the detection of any
crack at an early stage in the forward lug of
the RH (right-hand) and LH (left-hand) MLG
Rib 5 aft bearing attachment, the Type
Certificate holder has developed a new
inspection by means of ultrasonic method.
For the reasons described above, this new
inspection program is rendered mandatory by
this AD, which cancels and replaces the
requirement of EAD 2006–0335–E.
The corrective action includes
repairing or replacing MLG Rib 5, as
applicable. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
Airbus has issued Service Bulletins
A310–57–2090, Revision 01, dated
December 19, 2007, and A310–57–2091,
including Appendix 01, dated May 22,
2007. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
FAA’s Determination and Requirements
of This 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.
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 proposed
different actions in this AD from those
in the MCAI in order to follow FAA
E:\FR\FM\07APP1.SGM
07APP1
18724
Federal Register / Vol. 73, No. 67 / Monday, April 7, 2008 / Proposed Rules
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 68 products of U.S. registry.
We also estimate that it would take
about 5 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$27,200, or $400 per product.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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.
rfrederick on PROD1PC67 with PROPOSALS
policies. Any such differences are
highlighted in a NOTE within the
proposed AD.
§ 39.13
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
VerDate Aug<31>2005
15:07 Apr 04, 2008
Jkt 214001
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.
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14896 (72 FR
2612, January 22, 2007) and adding the
following new AD:
Airbus: Docket No. FAA–2008–0406;
Directorate Identifier 2007–NM–196–AD.
Comments Due Date
(a) We must receive comments by May 7,
2008.
Affected ADs
(b) The proposed AD supersedes AD 2007–
02–09, Amendment 39–14896.
Applicability
(c) This AD applies to Airbus Model A310
airplanes, certificated in any category, all
certified models, all serial numbers; except
for those where LH (left-hand) and RH (righthand) wing MLG (main landing gear) rib 5
forward lugs have been repaired by
installation of oversized interference fit
bushings as per Airbus Repair Instruction
R57249121, or which have had Airbus
Service Bulletin A310–57–2090 (AIRBUS
modification 13329) embodied in service.
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
During routine visual inspection, a crack
has been found in the wing MLG (main
landing gear) rib 5 forward attachment lug on
two A310 in-service aircraft. Laboratory
examination of one of the cracked ribs
confirmed that the crack is due to the
presence of pitting corrosion in the forward
lug holes. Also on both aircraft medium to
heavy corrosion was found in the forward
lugs on the opposite wing after removal of
the bushes. This situation if not detected,
could affect the structural integrity of the
MLG attachment. As an interim measure,
Airbus published Alert Service Bulletin
(ASB) A310–57A2088 to introduce a
repetitive detailed visual inspection (DVI) of
the forward attachment lug of MLG Rib 5.
EASA issued Emergency Airworthiness
Directive (EAD) 2006–0335–E [which
corresponds to FAA AD 2007–02–09] to
require the accomplishment of this repetitive
DVI.
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
In order to ensure the detection of any
crack at an early stage in the forward lug of
the RH (right-hand) and LH (left-hand) MLG
Rib 5 aft bearing attachment, the Type
Certificate holder has developed a new
inspection by means of ultrasonic method.
For the reasons described above, this new
inspection program is rendered mandatory by
this AD, which cancels and replaces the
requirement of EAD 2006–0335–E.
The corrective action includes repairing or
replacing MLG Rib 5, as applicable.
Restatement of Requirements of AD 2007–
02–09
(f) Unless already done, do the following
actions specified in paragraphs (f)(1), (f)(2),
and (f)(3) of this AD in accordance with the
instructions defined in Airbus Service
Bulletin A310–57A2088, dated November 6,
2006.
(1) Before the accumulation of 12,000 total
flight cycles, or within 14 days after February
6, 2007 (the effective date of AD 2007–02–
09), whichever occurs later: Perform a
detailed visual inspection of the LH and RH
wing MLG rib 5 aft bearing forward lugs.
(2) If any crack is detected at LH and/or RH
aft bearing forward lug, contact Airbus and
proceed with the replacement before next
flight.
(3) Repeat the inspection at intervals not
exceeding 100 flight cycles.
New Requirements of this AD: Actions and
Compliance
(g) Unless already done, before the
accumulation of 12,000 total flight cycles or
before the accumulation of 12,000 flight
cycles on MLG Rib 5, or within 14 days after
the effective date of this AD, whichever
occurs latest: Perform either a detailed visual
inspection (DVI) or an ultrasonic inspection
of the LH and RH MLG Rib 5 aft bearing
forward lug for cracks, in accordance with
the instructions defined in Airbus Service
Bulletin A310–57–2091, including Appendix
01, dated May 22, 2007. If a MLG Rib 5 has
been replaced on one side only, then the RH
and LH must be considered separately. Doing
this inspection ends the requirements of
paragraph (f) for that MLG Rib 5 only.
Note 1: The ultrasonic inspection will
detect any crack at an early stage and will
limit the risk of extensive repairs. This earlier
crack detection is not possible with the DVI.
(1) If no crack is detected during any
inspection required by paragraph (g) of this
AD: Repeat the applicable inspection at the
time specified in paragraph (g)(1)(i) or
(g)(1)(ii) of this AD.
(i) Repeat the DVI thereafter at intervals not
to exceed 100 flight cycles.
(ii) Repeat the ultrasonic inspection
thereafter at intervals not to exceed 825 flight
cycles.
(2) Replacement of the MLG Rib 5 in
accordance with the instructions defined in
Airbus Service Bulletin A310–57–2090,
Revision 01, dated December 19, 2007, ends
the repetitive inspections required by
paragraph (g)(1) of this AD for that MLG Rib
5 only.
(3) If any crack is detected during the DVI
required by paragraph (g) of this AD: Before
further flight, contact Airbus for replacement
E:\FR\FM\07APP1.SGM
07APP1
Federal Register / Vol. 73, No. 67 / Monday, April 7, 2008 / Proposed Rules
instructions and replace before further flight.
If MLG Rib 5 is not replaced in accordance
with the instructions defined in Airbus
Service Bulletin A310–57–2090, Revision 01,
dated December 19, 2007; repeat the
applicable inspection in paragraph (g) of this
AD at the time specified in the applicable
paragraph.
(4) If any crack is detected during the
ultrasonic inspection required by paragraph
(g) of this AD, before further flight,
accomplish the actions specified in
paragraphs (g)(4)(i) or (g)(4)(ii) of this AD, as
applicable.
(i) If any crack is not visible on MLG Rib
5: Before further flight, repair MLG Rib 5
using Repair Instruction R572–49121, Issue
C, dated May 2007. After embodiment of
Repair Instruction R572–49121, no further
actions are required by this AD and Airbus
Service Bulletin A310–57–2091, including
Appendix 01, dated May 22, 2007, for that
MLG Rib 5 only.
(ii) If any crack is visible on MLG Rib 5:
Before further flight, contact Airbus for rib
replacement instructions, and replace before
further flight. If MLG Rib 5 is not replaced
in accordance with the instructions defined
in Airbus Service Bulletin A310–57–2090,
Revision 01, dated December 19, 2007, repeat
the applicable inspection in paragraph (g) of
this AD at the time specified. Accomplishing
the replacement defined in Airbus Service
Bulletin A310–57–2090 ends the repetitive
inspections required by paragraph (g)(1) of
this AD for that MLG Rib 5 only.
FAA AD Differences
rfrederick on PROD1PC67 with PROPOSALS
Other FAA AD Provisions
(h) 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: 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. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(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
15:07 Apr 04, 2008
Related Information
(i) Refer to MCAI EASA Airworthiness
Directive 2007–0195, dated July 19, 2007,
and Airbus Service Bulletins A310–57–2090,
Revision 01, dated December 19, 2007, and
A310–57–2091, including Appendix 01,
dated May 22, 2007, for related information.
Issued in Renton, Washington, on March
27, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–7163 Filed 4–4–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Jkt 214001
runway excursion if takeoff must be
aborted.
DATES: We must receive comments on
this proposed AD by May 22, 2008.
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 AD, contact Boeing Commercial
Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and
Service Management, Dept. C1–L5A
(D800–0024).
14 CFR Part 39
Examining the AD Docket
[Docket No. FAA–2008–0407; Directorate
Identifier 2008–NM–002–AD]
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:
David Rathfelder, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; telephone (562)
627–5229; fax (562) 627–5210.
SUPPLEMENTARY INFORMATION:
RIN 2120–AA64
Note 2: This AD differs from the MCAI
and/or service information as follows:
Although the MCAI or service information
allows flight with cracks on aft bearing
forward lugs for a certain period of time, this
AD requires replacing MLG Rib 5 before
further flight if any crack is found.
Although the MCAI or service information
specifies submitting an inspection report
sheet to Airbus, this AD would not require
that action.
VerDate Aug<31>2005
(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,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
18725
Airworthiness Directives; McDonnell
Douglas Model 717–200 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
McDonnell Douglas Model 717–200
airplanes. This proposed AD would
require inspecting the drive assembly of
the aft elevator standby loop for
interference between the clevis and bolt
of the bellcrank assembly, correct
orientation of the pull-pull cable clevis
bolt, and excessive freeplay of the
bellcrank assembly bearing, and
corrective actions if necessary. This
proposed AD would also require
modifying the pull-pull cable clevis in
the drive assembly of the aft elevator
standby loop for certain airplanes. This
proposed AD results from a report of an
aborted takeoff due to a control column
disconnect. We are proposing this AD to
prevent binding of the bolt that connects
the cable 264A clevis to the bellcrank
assembly against the adjacent (upper)
clevis of the pull-pull cable assembly.
This binding condition could result in
slow airplane rotation or a control
column disconnect during takeoff and a
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
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–2008–0407; Directorate Identifier
2008–NM–002–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
E:\FR\FM\07APP1.SGM
07APP1
]]>Agencies
[Federal Register Volume 73, Number 67 (Monday, April 7, 2008)]
[Proposed Rules]
[Pages 18722-18725]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-7163]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0406; Directorate Identifier 2007-NM-196-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 18723]]
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This
proposed 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:
During routine visual inspection, a crack has been found in the
wing MLG (main landing gear) rib 5 forward attachment lug on two
A310 in-service aircraft. Laboratory examination of one of the
cracked ribs confirmed that the crack is due to the presence of
pitting corrosion in the forward lug holes. Also on both aircraft
medium to heavy corrosion was found in the forward lugs on the
opposite wing after removal of the bushes. This situation if not
detected, could affect the structural integrity of the MLG
attachment. * * *
* * * * *
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by May 7, 2008.
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 W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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 this proposed AD, 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.
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-2008-0406;
Directorate Identifier 2007-NM-196-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 based on 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 December 7, 2006, we issued AD 2007-02-09, Amendment 39-14896
(72 FR 2612, January 22, 2007). That AD required actions intended to
address an unsafe condition on the products listed above.
Since we issued AD 2007-02-09, the type certificate holder has
developed a new inspection using ultrasonic techniques. We have
determined that the existing AD must be superseded to add repair or
replacement of cracked main landing gear (MLG) Rib 5, provide the new
inspection as an option, and reduce the applicability of the AD to
exclude airplanes on which Airbus Service Bulletin A310-57-2090 has
been done.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2007-0195, dated July 19, 2007 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
During routine visual inspection, a crack has been found in the
wing MLG (main landing gear) rib 5 forward attachment lug on two
A310 in-service aircraft. Laboratory examination of one of the
cracked ribs confirmed that the crack is due to the presence of
pitting corrosion in the forward lug holes. Also on both aircraft
medium to heavy corrosion was found in the forward lugs on the
opposite wing after removal of the bushes. This situation if not
detected, could affect the structural integrity of the MLG
attachment. As an interim measure, Airbus published Alert Service
Bulletin (ASB) A310-57A2088 to introduce a repetitive detailed
visual inspection (DVI) of the forward attachment lug of MLG Rib 5.
EASA issued Emergency Airworthiness Directive (EAD) 2006-0335-E
[which corresponds to FAA AD 2007-02-09] to require the
accomplishment of this repetitive DVI.
In order to ensure the detection of any crack at an early stage
in the forward lug of the RH (right-hand) and LH (left-hand) MLG Rib
5 aft bearing attachment, the Type Certificate holder has developed
a new inspection by means of ultrasonic method. For the reasons
described above, this new inspection program is rendered mandatory
by this AD, which cancels and replaces the requirement of EAD 2006-
0335-E.
The corrective action includes repairing or replacing MLG Rib 5, as
applicable. You may obtain further information by examining the MCAI in
the AD docket.
Relevant Service Information
Airbus has issued Service Bulletins A310-57-2090, Revision 01,
dated December 19, 2007, and A310-57-2091, including Appendix 01, dated
May 22, 2007. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This 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.
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 proposed different actions in this AD from those
in the MCAI in order to follow FAA
[[Page 18724]]
policies. Any such differences are highlighted in a NOTE within the
proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 68 products of U.S. registry. We also estimate that
it would take about 5 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $27,200, or $400 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 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Amendment 39-14896 (72 FR
2612, January 22, 2007) and adding the following new AD:
Airbus: Docket No. FAA-2008-0406; Directorate Identifier 2007-NM-
196-AD.
Comments Due Date
(a) We must receive comments by May 7, 2008.
Affected ADs
(b) The proposed AD supersedes AD 2007-02-09, Amendment 39-
14896.
Applicability
(c) This AD applies to Airbus Model A310 airplanes, certificated
in any category, all certified models, all serial numbers; except
for those where LH (left-hand) and RH (right-hand) wing MLG (main
landing gear) rib 5 forward lugs have been repaired by installation
of oversized interference fit bushings as per Airbus Repair
Instruction R57249121, or which have had Airbus Service Bulletin
A310-57-2090 (AIRBUS modification 13329) embodied in service.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During routine visual inspection, a crack has been found in the
wing MLG (main landing gear) rib 5 forward attachment lug on two
A310 in-service aircraft. Laboratory examination of one of the
cracked ribs confirmed that the crack is due to the presence of
pitting corrosion in the forward lug holes. Also on both aircraft
medium to heavy corrosion was found in the forward lugs on the
opposite wing after removal of the bushes. This situation if not
detected, could affect the structural integrity of the MLG
attachment. As an interim measure, Airbus published Alert Service
Bulletin (ASB) A310-57A2088 to introduce a repetitive detailed
visual inspection (DVI) of the forward attachment lug of MLG Rib 5.
EASA issued Emergency Airworthiness Directive (EAD) 2006-0335-E
[which corresponds to FAA AD 2007-02-09] to require the
accomplishment of this repetitive DVI.
In order to ensure the detection of any crack at an early stage
in the forward lug of the RH (right-hand) and LH (left-hand) MLG Rib
5 aft bearing attachment, the Type Certificate holder has developed
a new inspection by means of ultrasonic method. For the reasons
described above, this new inspection program is rendered mandatory
by this AD, which cancels and replaces the requirement of EAD 2006-
0335-E.
The corrective action includes repairing or replacing MLG Rib 5,
as applicable.
Restatement of Requirements of AD 2007-02-09
(f) Unless already done, do the following actions specified in
paragraphs (f)(1), (f)(2), and (f)(3) of this AD in accordance with
the instructions defined in Airbus Service Bulletin A310-57A2088,
dated November 6, 2006.
(1) Before the accumulation of 12,000 total flight cycles, or
within 14 days after February 6, 2007 (the effective date of AD
2007-02-09), whichever occurs later: Perform a detailed visual
inspection of the LH and RH wing MLG rib 5 aft bearing forward lugs.
(2) If any crack is detected at LH and/or RH aft bearing forward
lug, contact Airbus and proceed with the replacement before next
flight.
(3) Repeat the inspection at intervals not exceeding 100 flight
cycles.
New Requirements of this AD: Actions and Compliance
(g) Unless already done, before the accumulation of 12,000 total
flight cycles or before the accumulation of 12,000 flight cycles on
MLG Rib 5, or within 14 days after the effective date of this AD,
whichever occurs latest: Perform either a detailed visual inspection
(DVI) or an ultrasonic inspection of the LH and RH MLG Rib 5 aft
bearing forward lug for cracks, in accordance with the instructions
defined in Airbus Service Bulletin A310-57-2091, including Appendix
01, dated May 22, 2007. If a MLG Rib 5 has been replaced on one side
only, then the RH and LH must be considered separately. Doing this
inspection ends the requirements of paragraph (f) for that MLG Rib 5
only.
Note 1: The ultrasonic inspection will detect any crack at an
early stage and will limit the risk of extensive repairs. This
earlier crack detection is not possible with the DVI.
(1) If no crack is detected during any inspection required by
paragraph (g) of this AD: Repeat the applicable inspection at the
time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) Repeat the DVI thereafter at intervals not to exceed 100
flight cycles.
(ii) Repeat the ultrasonic inspection thereafter at intervals
not to exceed 825 flight cycles.
(2) Replacement of the MLG Rib 5 in accordance with the
instructions defined in Airbus Service Bulletin A310-57-2090,
Revision 01, dated December 19, 2007, ends the repetitive
inspections required by paragraph (g)(1) of this AD for that MLG Rib
5 only.
(3) If any crack is detected during the DVI required by
paragraph (g) of this AD: Before further flight, contact Airbus for
replacement
[[Page 18725]]
instructions and replace before further flight. If MLG Rib 5 is not
replaced in accordance with the instructions defined in Airbus
Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007;
repeat the applicable inspection in paragraph (g) of this AD at the
time specified in the applicable paragraph.
(4) If any crack is detected during the ultrasonic inspection
required by paragraph (g) of this AD, before further flight,
accomplish the actions specified in paragraphs (g)(4)(i) or
(g)(4)(ii) of this AD, as applicable.
(i) If any crack is not visible on MLG Rib 5: Before further
flight, repair MLG Rib 5 using Repair Instruction R572-49121, Issue
C, dated May 2007. After embodiment of Repair Instruction R572-
49121, no further actions are required by this AD and Airbus Service
Bulletin A310-57-2091, including Appendix 01, dated May 22, 2007,
for that MLG Rib 5 only.
(ii) If any crack is visible on MLG Rib 5: Before further
flight, contact Airbus for rib replacement instructions, and replace
before further flight. If MLG Rib 5 is not replaced in accordance
with the instructions defined in Airbus Service Bulletin A310-57-
2090, Revision 01, dated December 19, 2007, repeat the applicable
inspection in paragraph (g) of this AD at the time specified.
Accomplishing the replacement defined in Airbus Service Bulletin
A310-57-2090 ends the repetitive inspections required by paragraph
(g)(1) of this AD for that MLG Rib 5 only.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows:
Although the MCAI or service information allows flight with
cracks on aft bearing forward lugs for a certain period of time,
this AD requires replacing MLG Rib 5 before further flight if any
crack is found.
Although the MCAI or service information specifies submitting an
inspection report sheet to Airbus, this AD would not require that
action.
Other FAA AD Provisions
(h) 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: 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.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(i) Refer to MCAI EASA Airworthiness Directive 2007-0195, dated
July 19, 2007, and Airbus Service Bulletins A310-57-2090, Revision
01, dated December 19, 2007, and A310-57-2091, including Appendix
01, dated May 22, 2007, for related information.
Issued in Renton, Washington, on March 27, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-7163 Filed 4-4-08; 8:45 am]
BILLING CODE 4910-13-P
