Airworthiness Directives; Dassault Model Mystere-Falcon 50, Mystere-Falcon 900, Falcon 900EX, Falcon 2000, and Falcon 2000EX Airplanes, 52311-52314 [E7-18045]
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Federal Register / Vol. 72, No. 177 / Thursday, September 13, 2007 / Proposed Rules
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Some taperlocks used in the wing-tofuselage junction at rib 1 were found to be
non-compliant with the applicable
specification, resulting in a loss of pretension in the fasteners. In such conditions,
the structural integrity of the aircraft could be
affected.
This Airworthiness Directive mandates a
repetitive internal inspection of the lower
stiffeners, and a repetitive external
inspection of the lower panels in center and
outer wing box at level of rib 1 junction.
The corrective action includes contacting
Airbus for repair instructions and repair if
any crack is found.
ebenthall on PRODPC61 with PROPOSALS
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) For A320–200 aircraft: Before the
defined threshold or within the defined grace
period after the effective date of this AD,
whichever occurs later, as listed in paragraph
1.E., ‘‘Compliance,’’ of Airbus Service
Bulletin A320–57–1129, Revision 01, dated
July 28, 2006, and following the instructions
given in the service bulletin, perform an
internal ultrasonic inspection of the lower
stiffeners in the center and outer wing box at
the level of the rib 1 junction to detect cracks,
and if any crack is found, before further flight
contact Airbus for repair instructions and
repair. Repeat this inspection at the intervals
defined in paragraph 1.E., ‘‘Compliance,’’ of
the service bulletin.
(2) For all aircraft: Before the defined
threshold or within the defined grace period
after the effective date of this AD, whichever
occurs later, as listed in paragraph 1.E.,
‘‘Compliance,’’ of Airbus Service Bulletin
A320–57–1130, Revision 01, dated July 28,
2006, and following the instructions given in
the service bulletin, perform an external
ultrasonic inspection of the lower stiffeners
in the center and outer wing box at the level
of the rib 1 junction to detect cracks, and if
any crack is found, before further flight
contact Airbus for repair instructions and
repair. Repeat this inspection at the intervals
defined in paragraph 1.E., ‘‘Compliance,’’ of
the service bulletin. Aircraft that have
already accomplished Airbus Service
Bulletin A320–57–1130, dated September 10,
2004, are compliant with this paragraph.
(3) Modification of the aircraft in
accordance with the instructions contained
in Airbus Service Bulletins A320–57–1131,
A320–57–1137, or A320–57–1140, all dated
November 21, 2006; terminates the repetitive
inspection requirements of this AD.
that the corrective action be done before
further flight.
Although the MCAI and/or service
information specify a compliance time for
accomplishing the inspections after the
effective date on the MCAI, this AD requires
compliance within the specified compliance
time after the effective date of this AD.
DEPARTMENT OF TRANSPORTATION
Other FAA AD Provisions
RIN 2120–AA64
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tim Dulin,
Aerospace Engineer, International Branch,
ANM–116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2141; 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.
Airworthiness Directives; Dassault
Model Mystere-Falcon 50, MystereFalcon 900, Falcon 900EX, Falcon
2000, and Falcon 2000EX Airplanes
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2007–0067R1, dated June 7, 2007;
and Airbus Service Bulletins A320–57–1129
and A320–57–1130, both Revision 01, both
dated July 28, 2006; for related information.
Issued in Renton, Washington, on
September 4, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–18046 Filed 9–12–07; 8:45 am]
BILLING CODE 4910–13–P
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows:
Although the MCAI or service information
does not specify a compliance time for
corrective action (repair of cracks),
paragraphs (f)(1) and (f)(2) of this AD require
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29175; Directorate
Identifier 2007–NM–134–AD]
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. 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:
A rotating rod in the trailing edge flap
control linkage broke in flight. Investigations
revealed that the rotating rod had been
installed in the wrong side during a
maintenance operation. This incorrect
installation caused a contact between the
rotating rod and its retaining bracket leading,
after some time in operation, to the rod
breakage and flap asymmetry situation.
The consequence on the airplane of the
flap asymmetry combined with a latent
failure of the asymmetry detection system is
classified as a catastrophic failure condition.
The unsafe condition is failure of the
rotating rod in the control linkage of the
trailing edge flap and consequent flap
asymmetry during the approach to
landing, which could result in reduced
controllability of the airplane. 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 October 15, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• 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: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
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Federal Register / Vol. 72, No. 177 / Thursday, September 13, 2007 / Proposed Rules
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.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,
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
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1137; 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–2007–29175; Directorate Identifier
2007–NM–134–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://
dms.dot.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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2006–0115,
dated May 10, 2006 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
A rotating rod in the trailing edge flap
control linkage broke in flight. Investigations
revealed that the rotating rod had been
installed in the wrong side during a
maintenance operation. This incorrect
installation caused a contact between the
rotating rod and its retaining bracket leading,
after some time in operation, to the rod
breakage and flap asymmetry situation.
The consequence on the airplane of the
flap asymmetry combined with a latent
failure of the asymmetry detection system is
classified as a catastrophic failure condition.
The unsafe condition is failure of the
rotating rod in the control linkage of the
trailing edge flap and consequent flap
asymmetry during the approach to
landing, which could result in reduced
controllability of the airplane. The
corrective actions include the following:
Verifying the correct assembly of the
flap rotating rods and associated
brackets and installing the rod and
bracket with correct orientation/
positioning if necessary; and inspecting
the rod for damage and replacing the
rod if any damage is found. You may
obtain further information by examining
the MCAI in the AD docket.
Relevant Service Information
Dassault has issued the following
service information:
Airplane model
Service Bulletin No.
Mystere-Falcon 50 ..................................................................
Mystere-Falcon 900 ................................................................
Falcon 900EX .........................................................................
Falcon 2000 ............................................................................
Falcon 2000EX .......................................................................
F50–468 .................................................................................
F900–367 ...............................................................................
F900EX–269 ..........................................................................
F2000–326 .............................................................................
F2000EX–83 ..........................................................................
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
ebenthall on PRODPC61 with PROPOSALS
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
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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
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 739 products of U.S.
registry. We also estimate that it would
take about 2 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
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Date
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March
March
March
March
29,
29,
29,
29,
29,
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2006.
2006.
2006.
2006.
proposed AD on U.S. operators to be
$118,240, or $160 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
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Federal Register / Vol. 72, No. 177 / Thursday, September 13, 2007 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701.
products identified in this rulemaking
action.
§ 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.
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:
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Dassault Aviation: Docket No. FAA–2007–
29175; Directorate Identifier 2007–NM–
134–AD.
Comments Due Date
(a) We must receive comments by October
15, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes
identified in paragraphs (c)(1), (c)(2), (c)(3),
and (c)(4) of this AD; certificated in any
category.
(1) Dassault Model Mystere-Falcon 50
airplanes on which Dassault Modification
M2996 has not been implemented.
(2) Dassault Model Mystere-Falcon 900
airplanes on which Dassault Modification
M5007 has not been implemented.
(3) Dassault Model Falcon 900EX airplanes
on which Dassault Modification M5007 has
not been implemented (including serial
number 601 and subsequent, also known as
‘‘DX’’ airplanes).
(4) Dassault Model Falcon 2000 and Falcon
2000EX airplanes on which Dassault
Modification M2465 has not been
implemented.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
A rotating rod in the trailing edge flap
control linkage broke in flight. Investigations
revealed that the rotating rod had been
installed in the wrong side during a
maintenance operation. This incorrect
installation caused a contact between the
rotating rod and its retaining bracket leading,
after some time in operation, to the rod
breakage and flap asymmetry situation.
The consequence on the airplane of the
flap asymmetry combined with a latent
failure of the asymmetry detection system is
classified as a catastrophic failure condition.
The unsafe condition is failure of the rotating
rod in the control linkage of the trailing edge
flap and consequent flap asymmetry during
the approach to landing, which could result
in reduced controllability of the airplane.
The corrective actions include the following:
Verifying the correct assembly of the flap
rotating rods and associated brackets and
installing the rod and bracket with correct
orientation/positioning if necessary; and
inspecting the rod for damage and replacing
the rod if any damage is found.
Actions and Compliance
(f) Unless already done, within 330 flight
hours or 7 months after the effective date of
this AD, whichever occurs first, do the
following actions.
(1) Verify the correct assembly of the flap
rotating rods and associated retaining
brackets installed in the LH (left-hand)/RH
(right-hand) wing root compartment and in
the LH and RH main landing gear
compartment and inspect the rod for damage,
in accordance with the applicable Dassault
Service Bulletin given in Table 1 of this AD.
(2) If a rod is found damaged, replace this
rod prior to next flight in accordance with
the applicable Dassault Service Bulletin
given in Table 1 of this AD. If the rod
orientation or bracket positioning is not
correct, correct the orientation or positioning,
as applicable, prior to next flight in
accordance with the applicable Dassault
Service Bulletin given in Table 1 of this AD.
(3) Label the rods and associated retaining
brackets in accordance with the applicable
Dassault Service Bulletin given in Table 1 of
this AD.
TABLE 1.—DASSAULT SERVICE BULLETINS
Airplane Model
Service Bulletin No.
Mystere-Falcon 50 ..................................................................
Mystere-Falcon 900 ................................................................
Falcon 900EX .........................................................................
Falcon 2000 ............................................................................
Falcon 2000EX .......................................................................
F50–468 .................................................................................
F900–367 ...............................................................................
F900EX–269 ..........................................................................
F2000–326 .............................................................................
F2000EX–83 ..........................................................................
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
ebenthall on PRODPC61 with PROPOSALS
Other FAA AD Provisions
(g) 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
VerDate Aug<31>2005
15:17 Sep 12, 2007
Jkt 211001
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tom Rodriguez,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone (425)
227–1137; 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
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Date
March
March
March
March
March
29,
29,
29,
29,
29,
2006.
2006.
2006.
2006.
2006.
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.
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Federal Register / Vol. 72, No. 177 / Thursday, September 13, 2007 / Proposed Rules
Related Information
(h) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2006–
0115, dated May 10, 2006; and the Dassault
Service Bulletins listed in Table 1 of this AD,
for related information.
Issued in Renton, Washington, on August
31, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–18045 Filed 9–12–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29174; Directorate
Identifier 2007–NM–125–AD]
RIN 2120–AA64
Comments Invited
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
ebenthall on PRODPC61 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. This proposed AD would
require repetitive inspections to detect
cracking of the body station 303.9 frame,
and corrective action if necessary. This
proposed AD also provides for optional
terminating action for the repetitive
inspections. This proposed AD results
from reports of cracks found at the
cutout in the web of body station frame
303.9 inboard of stringer 16L. We are
proposing this AD to detect and correct
such cracking, which could prevent the
left forward entry door from sealing
correctly, and could cause in-flight
decompression of the airplane.
DATES: We must receive comments on
this proposed AD by October 29, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
VerDate Aug<31>2005
15:17 Sep 12, 2007
Jkt 211001
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Howard Hall, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6430; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2007–29174; Directorate
Identifier 2007–NM–125–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
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ground floor of the West Building at the
DOT street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
the Docket Management System receives
them.
Discussion
We have received reports of cracks
found at the cutout in the web of the
body station 303.9 frame inboard of
stringer 16L on seven Boeing Model 737
‘‘classic’’ airplanes. The cracks were
found on airplanes that had
accumulated between 37,562 and 64,000
total flight cycles. Such cracking, if not
corrected, could prevent the left forward
entry door from sealing correctly, and
could cause in-flight decompression of
the airplane.
Relevant Service Information
We have reviewed two service
bulletins related to this action. The
service bulletins are similar but affect
different groups of airplanes.
Boeing Alert Service Bulletin 737–
53A1188, Revision 2, dated May 9,
2007, for certain Model 737–300, –400,
and –500 series airplanes, describes the
following actions:
• Repetitive high-frequency eddy
current (HFEC) and detailed inspections
to detect cracking in the station 303.9
web and doubler around the cutouts for
door stop straps at stringers 15L and
16L.
• A repair/preventive change, which
includes installing a new web, doubler,
and stop fitting assemblies; changing the
shape of the web cutout; and doing an
eddy current inspection.
Service Bulletin 737–53A1188
specifies a threshold for the initial
inspection of 10,000 total flight cycles
and a grace period of 2,250 flight cycles.
Boeing Alert Service Bulletin 737–
53A1197, dated August 25, 2006, for
certain Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
describes the following actions:
• Repetitive ultrasound inspections of
the slot-shaped cutout in the web for the
door stop strap at stringer 16L.
• Repetitive HFEC inspections of the
web along the upper edge and lower
edge of the doubler around the doorstop
strap at stringer 16L.
• Repetitive detailed inspections of
the web around the doubler for the
cutout at stringer 16.
• A repair/preventive change, which
involves installing a new web and
doubler.
Service Bulletin 737–53A1197
specifies a threshold for the initial
inspection of 30,000 total flight cycles
and a grace period of 2,250 flight cycles.
For both service bulletins, a repair/
preventive change eliminates the need
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[Federal Register Volume 72, Number 177 (Thursday, September 13, 2007)]
[Proposed Rules]
[Pages 52311-52314]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-18045]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29175; Directorate Identifier 2007-NM-134-AD]
RIN 2120-AA64
Airworthiness Directives; Dassault Model Mystere-Falcon 50,
Mystere-Falcon 900, Falcon 900EX, Falcon 2000, and Falcon 2000EX
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. 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:
A rotating rod in the trailing edge flap control linkage broke
in flight. Investigations revealed that the rotating rod had been
installed in the wrong side during a maintenance operation. This
incorrect installation caused a contact between the rotating rod and
its retaining bracket leading, after some time in operation, to the
rod breakage and flap asymmetry situation.
The consequence on the airplane of the flap asymmetry combined
with a latent failure of the asymmetry detection system is
classified as a catastrophic failure condition.
The unsafe condition is failure of the rotating rod in the control
linkage of the trailing edge flap and consequent flap asymmetry during
the approach to landing, which could result in reduced controllability
of the airplane. 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 October 15,
2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
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: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE.,
[[Page 52312]]
Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays.
Federal eRulemaking Portal: https://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.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, 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 Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1137; 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-2007-
29175; Directorate Identifier 2007-NM-134-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://
dms.dot.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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2006-0115, dated May 10, 2006 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
A rotating rod in the trailing edge flap control linkage broke
in flight. Investigations revealed that the rotating rod had been
installed in the wrong side during a maintenance operation. This
incorrect installation caused a contact between the rotating rod and
its retaining bracket leading, after some time in operation, to the
rod breakage and flap asymmetry situation.
The consequence on the airplane of the flap asymmetry combined
with a latent failure of the asymmetry detection system is
classified as a catastrophic failure condition.
The unsafe condition is failure of the rotating rod in the control
linkage of the trailing edge flap and consequent flap asymmetry during
the approach to landing, which could result in reduced controllability
of the airplane. The corrective actions include the following:
Verifying the correct assembly of the flap rotating rods and associated
brackets and installing the rod and bracket with correct orientation/
positioning if necessary; and inspecting the rod for damage and
replacing the rod if any damage is found. You may obtain further
information by examining the MCAI in the AD docket.
Relevant Service Information
Dassault has issued the following service information:
------------------------------------------------------------------------
Service
Airplane model Bulletin No. Date
------------------------------------------------------------------------
Mystere-Falcon 50............ F50-468........ March 29, 2006.
Mystere-Falcon 900........... F900-367....... March 29, 2006.
Falcon 900EX................. F900EX-269..... March 29, 2006.
Falcon 2000.................. F2000-326...... March 29, 2006.
Falcon 2000EX................ F2000EX-83..... March 29, 2006.
------------------------------------------------------------------------
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 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 739 products of U.S. registry. We also estimate that
it would take about 2 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 $118,240, or $160 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
[[Page 52313]]
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 adding the following new AD:
Dassault Aviation: Docket No. FAA-2007-29175; Directorate Identifier
2007-NM-134-AD.
Comments Due Date
(a) We must receive comments by October 15, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any
category.
(1) Dassault Model Mystere-Falcon 50 airplanes on which Dassault
Modification M2996 has not been implemented.
(2) Dassault Model Mystere-Falcon 900 airplanes on which
Dassault Modification M5007 has not been implemented.
(3) Dassault Model Falcon 900EX airplanes on which Dassault
Modification M5007 has not been implemented (including serial number
601 and subsequent, also known as ``DX'' airplanes).
(4) Dassault Model Falcon 2000 and Falcon 2000EX airplanes on
which Dassault Modification M2465 has not been implemented.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
A rotating rod in the trailing edge flap control linkage broke
in flight. Investigations revealed that the rotating rod had been
installed in the wrong side during a maintenance operation. This
incorrect installation caused a contact between the rotating rod and
its retaining bracket leading, after some time in operation, to the
rod breakage and flap asymmetry situation.
The consequence on the airplane of the flap asymmetry combined
with a latent failure of the asymmetry detection system is
classified as a catastrophic failure condition.
The unsafe condition is failure of the rotating rod in the control
linkage of the trailing edge flap and consequent flap asymmetry
during the approach to landing, which could result in reduced
controllability of the airplane. The corrective actions include the
following: Verifying the correct assembly of the flap rotating rods
and associated brackets and installing the rod and bracket with
correct orientation/positioning if necessary; and inspecting the rod
for damage and replacing the rod if any damage is found.
Actions and Compliance
(f) Unless already done, within 330 flight hours or 7 months
after the effective date of this AD, whichever occurs first, do the
following actions.
(1) Verify the correct assembly of the flap rotating rods and
associated retaining brackets installed in the LH (left-hand)/RH
(right-hand) wing root compartment and in the LH and RH main landing
gear compartment and inspect the rod for damage, in accordance with
the applicable Dassault Service Bulletin given in Table 1 of this
AD.
(2) If a rod is found damaged, replace this rod prior to next
flight in accordance with the applicable Dassault Service Bulletin
given in Table 1 of this AD. If the rod orientation or bracket
positioning is not correct, correct the orientation or positioning,
as applicable, prior to next flight in accordance with the
applicable Dassault Service Bulletin given in Table 1 of this AD.
(3) Label the rods and associated retaining brackets in
accordance with the applicable Dassault Service Bulletin given in
Table 1 of this AD.
Table 1.--Dassault Service Bulletins
------------------------------------------------------------------------
Service
Airplane Model Bulletin No. Date
------------------------------------------------------------------------
Mystere-Falcon 50............ F50-468........ March 29, 2006.
Mystere-Falcon 900........... F900-367....... March 29, 2006.
Falcon 900EX................. F900EX-269..... March 29, 2006.
Falcon 2000.................. F2000-326...... March 29, 2006.
Falcon 2000EX................ F2000EX-83..... March 29, 2006.
------------------------------------------------------------------------
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) 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
Rodriguez, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; telephone (425) 227-1137; 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.
[[Page 52314]]
Related Information
(h) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2006-0115, dated May 10, 2006; and the Dassault Service
Bulletins listed in Table 1 of this AD, for related information.
Issued in Renton, Washington, on August 31, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-18045 Filed 9-12-07; 8:45 am]
BILLING CODE 4910-13-P
