Airworthiness Directives; CTRM Aviation Sdn. Bhd. (Formerly Eagle Aircraft (Malaysia) Sdn. Bhd.) Model Eagle 150B Airplanes, 39020-39023 [E6-10773]
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Federal Register / Vol. 71, No. 132 / Tuesday, July 11, 2006 / Proposed Rules
A notice of extension of comment
period was issued July 20, 2005, and
published in the Federal Register on
July 25, 2005 (70 FR 42513), which
extended the comment period to
September 25, 2005. The comment
period was extended again in a notice
issued September 23, 2005, and
published in the Federal Register on
September 27, 2005 (70 FR 56378),
which further extended the comment
period to November 28, 2005.
Prior to the end of the previous
comment period, USDA received a
request under the Freedom of
Information Act (FOIA) for all
information cited in the proposed rule.
USDA suspended action on the proposal
until the FOIA request, and a
subsequent appeal to USDA’s initial
response to the FOIA, could be resolved.
USDA has subsequently resolved all
issues regarding the FOIA request and
released all the information cited in the
proposed rule to the requesting party.
On October 31, 2005, USDA received
additional requests to again extend the
comment period. The additional
extension of the comment period was
requested to provide additional time to
resolve issues surrounding the ongoing
FOIA request and to accumulate and
analyze data regarding the proposal.
USDA is extending the comment
period an additional 60 days to allow
interested persons more time to review
the proposed rule, perform a more
complete analysis, and submit written
comments.
This notice is issued pursuant to the
Agricultural Marketing Agreement Act
of 1937.
Authority: 7 U.S.C. 601–674.
Dated: June 30, 2006.
Lloyd C. Day,
Administrator, Agricultural Marketing
Service.
[FR Doc. E6–10769 Filed 7–10–06; 8:45 am]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23786; Directorate
Identifier 2006–CE–11–AD]
jlentini on PROD1PC65 with PROPOSAL
RIN 2120–AA64
Airworthiness Directives; CTRM
Aviation Sdn. Bhd. (Formerly Eagle
Aircraft (Malaysia) Sdn. Bhd.) Model
Eagle 150B Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Aug<31>2005
17:15 Jul 10, 2006
Jkt 208001
Notice of proposed rulemaking
(NPRM).
ACTION:
SUMMARY: The FAA proposes to
supersede Airworthiness Directive (AD)
2004–11–04, which applies to all CTRM
Aviation Sdn. Bhd. (Formerly Eagle
Aircraft (Malaysia) Sdn. Bhd.) Model
Eagle 150B airplanes. AD 2004–11–04
currently requires you to inspect certain
canard inboard flap hinge support
brackets (initially before further flight
and repetitively before the first flight of
each day) and perform any necessary
follow-up action. This proposed AD
results from mandatory continuing
airworthiness information (MCAI)
issued by the airworthiness authority for
Malaysia to require the installation of
improved design inboard flap hinge
brackets as terminating action for the
repetitive inspections. Consequently,
this proposed AD would initially retain
the requirement that you inspect certain
canard inboard flap hinge support
brackets (initially before further flight
and repetitively before the first flight of
each day) and then require that you
replace the parts with new design
inboard flap hinge brackets as
terminating action for the repetitive
inspections or if cracks are found. We
are issuing this proposed AD to detect
and correct cracks in the canard inboard
flap hinge support brackets, which
could result in loss of retention of
controls and consequently, loss of
airplane control.
DATES: We must receive comments on
this proposed AD by August 10, 2006.
ADDRESSES: Use one of the following
addresses to comment 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: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact CTRM
Aviation Sdn. Bhd. (formerly known as
Eagle Aircraft (Malaysia) Sdn. Bhd.),
Locked Bag 1028, Pejabat Pos Besar
Melaka, 75150 Melaka, Malaysia;
PO 00000
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telephone: 06 317 1007; facsimile: 06
317 7023.
FOR FURTHER INFORMATION CONTACT: Karl
Schletzbaum, Aerospace Engineer,
ACE–112, Small Airplane Directorate,
901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: 816–329–
4146; facsimile: 816–329–4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number, ‘‘FAA–2006–23786; Directorate
Identifier 2006–CE–11–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 we receive
concerning this proposed AD.
Discussion
The Department of Civil Aviation
(DCA) for Malaysia issued AD No. CAM
AD 001–01–2004, dated January 19,
2004, against Eagle Aircraft (now CTRM
Aviation Sdn. Bhd.) Models X–TS, X–
TS 150, and 150B airplanes. CAM AD
001–01–2004 required the following for
these airplanes that are registered for
operation in Malaysia:
• A visual inspection of the gusset
weld area of the canard inboard flap
hinge support brackets for cracked,
lifted, or missing paint in the area of the
weld or suspected cracks;
• A more detailed inspection for
cracks (using fluorescent penetrant
inspection (FPI) methods) if any of the
above conditions exist; and
• Replacement of any canard inboard
flap hinge support bracket with cracks
and continued repetitive inspections of
the replacement bracket.
The DCA of Malaysia is currently the
country with State of Design
responsibilities on the affected
airplanes. Before the DCA, the Civil
Aviation Safety Authority (CASA) of
Australia had the State of Design
responsibilities. During this time, the
CASA issued CASA AD/X–TS/5, dated
October 2003, revised April 2, 2004, to
address the unsafe condition and
require the above actions on Models
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Federal Register / Vol. 71, No. 132 / Tuesday, July 11, 2006 / Proposed Rules
XTS–150 and 150B airplanes registered
for operation in Australia.
The Australian and Malaysian ADs
were issued based on reports of cracks
in the gusset weld area of the canard
inboard flap hinge support brackets on
several of the affected airplanes. Neither
authority has been able to attribute the
cracks to a specific cause. The probable
causes are:
• Manufacturing defects: the part
might have suffered from a burnthrough during welding or the
outperforming stress relieving process
after welding;
• Design problems: poor distribution
of stress concentration could create
fatigue hotspots; and
• Operational problems: pilot exceeds
Vfe (flap extension speed), inducing
loads higher than the certificated limit
load).
Also, no information exists regarding
damage tolerance on these brackets to
show the part can absorb any kind of
crack without leading to immediate
failure.
Based on the above, the CASA and
DCA both issued ADs for their
respective countries that require, before
further flight, initial inspections and,
before the first flight of each day,
repetitive inspections.
The CTRM Aviation Sdn. Bhd. Model
Eagle 150B airplane is the only affected
airplane model type certificated for
operation in the United States. There are
currently 13 of these airplanes on the
U.S. registry.
Based on all of this information from
the State of Design, the FAA issued AD
2004–11–04, Amendment 39–13649 (69
FR 30189, May 27, 2004). AD 2004–11–
04 currently requires that you do the
following on CTRM Aviation (formerly
Eagle Aircraft (Malaysia) Sdn. Bhd.)
Sdn. Bhd. Model Eagle 150B airplanes:
• Inspect certain canard inboard flap
hinge support brackets (initially before
further flight and repetitively before the
first flight of each day); and;
• Perform any necessary follow-up
action.
The DCA recently notified FAA of the
need to change AD 2004–11–04. The
DCA issued CAM AD 001–01–2004 R1,
dated December 23, 2005. This revision
includes an optional modification as
terminating action for the repetitive
inspections required by CAM AD 001–
01–2004.
This condition, if not corrected, could
result in loss of retention of controls
and, consequently, loss of airplane
control.
Relevant Service Information
We have reviewed:
• Eagle Aircraft Mandatory Service
Bulletin SB 1109, Revision Original,
Effective Date August 29, 2003; and
• Eagle Aircraft Mandatory Service
Bulletin SB 1120, Original, Effective
Date June 3, 2005.
The service information describes
procedures for:
• Inspecting the gusset weld area of
the canard inboard flap hinge support
brackets, part number (P/N) 5731D01–
05 and P/N 5731D01–02, for cracks;
and;
• Replacing any canard inboard flap
hinge support brackets, P/N 5731D01–
05 and P/N 5731D01–02, with new
design inboard flap hinge brackets, P/N
5731D05–01 and P/N 5731D06–01.
Foreign Airworthiness Authority
Information
The DCA classified these service
bulletins as mandatory and issued
Malaysian AD No. CAM AD 001–01–
2004 R1, dated December 23, 2005, to
ensure the continued airworthiness of
these airplanes in Malaysia.
Labor cost
1 work-hour × $80 = $80 ..............................................
These CTRM Aviation Sdn. Bhd.
Model Eagle 150B airplanes are
manufactured in Malaysia and are typecertificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement.
Under this bilateral airworthiness
agreement, the DCA has kept us
informed of the situation described
above.
FAA’s Determination and Requirements
of the Proposed AD
We are proposing this AD because we
have examined the DCA’s findings,
evaluated all information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design that are certificated for
operation in the United States.
This proposed AD would supersede
AD 2004–11–04 with a new AD that
would initially retain the requirement
that certain canard inboard flap hinge
support brackets be inspected (initially
before further flight and repetitively
before the first flight of each day) and
then require that you replace the parts
with new design inboard flap hinge
brackets as terminating action for the
repetitive inspections or if cracks are
found. This proposed AD would require
you to use the service information
described previously to perform these
actions.
Costs of Compliance
We estimate that this proposed AD
affects 13 airplanes in the U.S. registry.
We estimate the following costs to do
each proposed inspection:
Total cost per
airplane
Parts cost
(*)
$80
39021
Total cost on U.S. operators
13 × $80 = $1,040.
* Not applicable.
We estimate the following costs to do
the replacements that would be required
as a result of the proposed inspection or
the proposed mandatory replacement:
Labor cost
Parts cost
jlentini on PROD1PC65 with PROPOSAL
10 work-hours × $80 = $800 ........................................
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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16:39 Jul 10, 2006
Jkt 208001
Total cost per
airplane
$1,700
$2,500
Total cost on U.S. operators
13 × $2,500 = $32,500.
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
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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
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Federal Register / Vol. 71, No. 132 / Tuesday, July 11, 2006 / Proposed Rules
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
Examining the AD Docket
You may examine the AD docket that
contains the proposed AD, the
regulatory evaluation, any comments
received, and other information on the
Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
(800) 647–5227) is located at the street
address stated 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, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
proposes to amend 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
the following new airworthiness
directive:
CTRM Aviation SDN. BHD. (Formerly Eagle
Aircraft (Malaysia) SDN. BHD.): Docket
No. FAA–2006–23786; Directorate
Identifier 2006-CE–11-AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
proposed airworthiness directive (AD) action
by August 10, 2006.
Affected ADs
(b) This AD supersedes AD 2004–11–04;
Amendment 39–13649.
Applicability
(c) This AD affects Model Eagle 150B
airplanes, all serial numbers, that are
certificated in any category.
Unsafe Condition
(d) This AD results from mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
Malaysia. The actions specified in this AD
are intended to detect and correct cracks in
the canard inboard flap hinge support
brackets, which could result in loss of
retention of controls and consequently, loss
of airplane control.
Compliance
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2004–11–04, Amendment 39–13649 (69
FR 30189, May 27, 2004), and adding
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Inspection gusset weld area of the canard
inboard flap hinge support brackets, part
number (P/N) 5731D01–05 and P/N
5731D01–02, for cracked, lifted, or missing
paint in the area of the weld or suspected
cracks.
(2) If cracked, lifted, or missing paint in the
area of the weld or suspected cracks are
found during any inspection required in paragraph (e)(1) of this AD, inspect the affected
bracket more fully as specified in the service
bulletin.
(3) Replace any canard inboard flap hinge support brackets, P/N 5731D01–05 and P/N
5731D01–02, with new design inboard flap
hinge brackets, P/N 5731D05–01 and P/N
5731D06–01.
Initially inspect before the next flight after
June 4, 2004 (the effective date of AD
2004–11–04). Repetitively inspect thereafter
before the first flight of each day.
Follow Eagle Aircraft Mandatory Service Bulletin SB 1109, Revision Original, Effective
Date August 29, 2003.
Before further flight after any inspection required by paragraph (e)(1) where cracked,
lifted, or missing paint in the area of the
weld or suspected cracks are found.
Follow Eagle Aircraft Mandatory Service Bulletin SB 1109, Revision Original, Effective
Date August 29, 2003.
Before further flight after any inspection where
cracks are found or within 6 months after
the effective date of this AD, whichever occurs first. This action terminates the repetitive inspections required in paragraph
(e)(1) of this AD.
As of the effective date of this AD ...................
Follow Eagle Aircraft Mandatory Service Bulletin SB 1120, Original, Effective Date June
3, 2005.
jlentini on PROD1PC65 with PROPOSAL
(4) Do not install any canard inboard flap hinge
support brackets, P/N 5731D01–05 and P/N
5731D01–02.
(f) The Australian AD allows an
appropriately trained pilot to perform the
visual inspections of the canard inboard flap
hinge support brackets. Although the
Malaysian AD does not specifically state this,
it does refer to the Australian AD. Regardless,
the Federal Aviation Regulations (14 CFR
43.3) only allow the pilot to perform
VerDate Aug<31>2005
16:39 Jul 10, 2006
Jkt 208001
preventive maintenance as described in 14
CFR part 43, App. A, paragraph (c). These
visual inspections are not considered
preventive maintenance under 14 CFR part
43, App. A, paragraph (c). Therefore, an
appropriately-rated mechanic must perform
all actions of this AD.
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Not Applicable.
Special Flight Permit
(g) Special flight permits are not allowed
for this AD. Part 39 of the Federal Aviation
Regulations (14 CFR part 39) provides that
FAA may issue special flight permits for
ADs, unless otherwise specified in the
individual AD.s The FAA has determined
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Federal Register / Vol. 71, No. 132 / Tuesday, July 11, 2006 / Proposed Rules
that the safety issue is severe enough that
failure of the canard inboard flap hinge
support brackets must be prevented and
cracks in this area must be detected before
further operation.
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, Standards Office, Small
Airplane Directorate, FAA, ATTN: Karl
Schletzbaum, Aerospace Engineer, ACE–112,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: 816–329–4146; facsimile: 816–
329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(i) AMOCs approved for AD 2004–11–04
are approved for this AD.
Related Information
(j) Malaysian AD No. CAM AD 001–01–
2004 R1, dated December 23, 2005, and
Australian AD No. CASA AD/X–TS/5, dated
August 21, 2003, revised April 2, 2004, also
address the subject of this AD. To get copies
of the documents referenced in this AD,
contact CTRM Aviation Sdn. Bhd. (formerly
known as Eagle Aircraft Sdn. Bhd.), Locked
Bag 1028, Pejabat Pos Besar Melaka, 75150
Melaka, Malaysia; telephone: 06 317 1007;
facsimile: 06 317 7023. To view the AD
docket, go to the Docket Management
Facility; U.S. Department of Transportation,
400 Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC, or on the
Internet at https://dms.dot.gov. The docket
number is Docket No. FAA–2006–23786;
Directorate Identifier 2006–CE–11–AD.
Issued in Kansas City, Missouri, on July 3,
2006.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–10773 Filed 7–10–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24825; Directorate
Identifier 2006–NE–17–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG (Formerly
Rolls-Royce, plc.) Dart 528, 529, 532,
535, 542, and 555 Series Turbofan
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
jlentini on PROD1PC65 with PROPOSAL
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
Rolls-Royce Deutschland Ltd & Co KG
(RRD) Dart 528, 529, 532, 535, 542, and
VerDate Aug<31>2005
16:39 Jul 10, 2006
Jkt 208001
555 series turbofan engines. This
proposed AD would require a
dimensional inspection of the
intermediate pressure turbine (IPT) disk
or an ultrasonic inspection of the seal
arm contact between the high pressure
turbine (HPT) and the IPT disk seal arm
and rework or replacement of the IPT
disk if wear outside acceptable limits is
found. This proposed AD results from
reports of a number of HPT disk
failures, some of which resulted in
portions of the HPT disk being released.
We are proposing this AD to prevent
HPT disk failure, which can result in an
uncontained engine failure and damage
to the airplane.
DATES: We must receive any comments
on this proposed AD by September 11,
2006.
ADDRESSES: Use one of the following
addresses to comment 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: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Rolls-Royce Deutschland Ltd
& Co KG, Eschenweg 11, D–15827
Dahlewitz, Germany; telephone 49 (0)
33–7086–1768; fax 49 (0) 33–7086–3356
for the service information identified in
this proposed AD.
FOR FURTHER INFORMATION CONTACT:
Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
telephone (781) 238–7747; fax (781)
238–7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2006–24825; Directorate Identifier
2006–NE–17–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
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39023
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 the DMS
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 the 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 AD Docket
You may examine the docket that
contains the proposal, any comments
received, and any final disposition in
person at the DMS Docket Offices
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Office (telephone (800) 647–
5227) is on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Discussion
The Luftfahrt-Bundesamt (LBA),
which is the airworthiness authority for
Germany, recently notified us that an
unsafe condition may exist on RRD Dart
528, 529, 532, 535, 542, and 555
turbofan engines. The LBA advises that
since 1972, there have been a number of
HPT disk failures on in-service engines,
three of which resulted in release of the
HPT turbine disk. Fretting between the
HPT disk and the IPT disk seal arms
caused the release. We are proposing
this AD to prevent HPT disk failure,
which can result in an uncontained
engine failure and damage to the
airplane.
We have reviewed and approved the
technical contents of RRD DART Service
Bulletin (SB) Da72–536, Revision 1,
dated August 25, 2003, and SB Da72–
538, dated June 10, 2005. SB Da72–536
describes procedures for conducting an
ultrasonic inspection to determine if a
gap exists between the HPT and IPT
disk seal arms. SB Da72–538 describes
procedures for a dimensional inspection
of the IPT disk and rework or
replacement of the IPT disk if wear
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]]>Agencies
[Federal Register Volume 71, Number 132 (Tuesday, July 11, 2006)]
[Proposed Rules]
[Pages 39020-39023]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-10773]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23786; Directorate Identifier 2006-CE-11-AD]
RIN 2120-AA64
Airworthiness Directives; CTRM Aviation Sdn. Bhd. (Formerly Eagle
Aircraft (Malaysia) Sdn. Bhd.) Model Eagle 150B Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2004-11-04, which applies to all CTRM Aviation Sdn. Bhd. (Formerly
Eagle Aircraft (Malaysia) Sdn. Bhd.) Model Eagle 150B airplanes. AD
2004-11-04 currently requires you to inspect certain canard inboard
flap hinge support brackets (initially before further flight and
repetitively before the first flight of each day) and perform any
necessary follow-up action. This proposed AD results from mandatory
continuing airworthiness information (MCAI) issued by the airworthiness
authority for Malaysia to require the installation of improved design
inboard flap hinge brackets as terminating action for the repetitive
inspections. Consequently, this proposed AD would initially retain the
requirement that you inspect certain canard inboard flap hinge support
brackets (initially before further flight and repetitively before the
first flight of each day) and then require that you replace the parts
with new design inboard flap hinge brackets as terminating action for
the repetitive inspections or if cracks are found. We are issuing this
proposed AD to detect and correct cracks in the canard inboard flap
hinge support brackets, which could result in loss of retention of
controls and consequently, loss of airplane control.
DATES: We must receive comments on this proposed AD by August 10, 2006.
ADDRESSES: Use one of the following addresses to comment 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: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
CTRM Aviation Sdn. Bhd. (formerly known as Eagle Aircraft (Malaysia)
Sdn. Bhd.), Locked Bag 1028, Pejabat Pos Besar Melaka, 75150 Melaka,
Malaysia; telephone: 06 317 1007; facsimile: 06 317 7023.
FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer,
ACE-112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: 816-329-4146; facsimile: 816-329-4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number, ``FAA-
2006-23786; Directorate Identifier 2006-CE-11-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 we
receive concerning this proposed AD.
Discussion
The Department of Civil Aviation (DCA) for Malaysia issued AD No.
CAM AD 001-01-2004, dated January 19, 2004, against Eagle Aircraft (now
CTRM Aviation Sdn. Bhd.) Models X-TS, X-TS 150, and 150B airplanes. CAM
AD 001-01-2004 required the following for these airplanes that are
registered for operation in Malaysia:
A visual inspection of the gusset weld area of the canard
inboard flap hinge support brackets for cracked, lifted, or missing
paint in the area of the weld or suspected cracks;
A more detailed inspection for cracks (using fluorescent
penetrant inspection (FPI) methods) if any of the above conditions
exist; and
Replacement of any canard inboard flap hinge support
bracket with cracks and continued repetitive inspections of the
replacement bracket.
The DCA of Malaysia is currently the country with State of Design
responsibilities on the affected airplanes. Before the DCA, the Civil
Aviation Safety Authority (CASA) of Australia had the State of Design
responsibilities. During this time, the CASA issued CASA AD/X-TS/5,
dated October 2003, revised April 2, 2004, to address the unsafe
condition and require the above actions on Models
[[Page 39021]]
XTS-150 and 150B airplanes registered for operation in Australia.
The Australian and Malaysian ADs were issued based on reports of
cracks in the gusset weld area of the canard inboard flap hinge support
brackets on several of the affected airplanes. Neither authority has
been able to attribute the cracks to a specific cause. The probable
causes are:
Manufacturing defects: the part might have suffered from a
burn-through during welding or the outperforming stress relieving
process after welding;
Design problems: poor distribution of stress concentration
could create fatigue hotspots; and
Operational problems: pilot exceeds Vfe (flap extension
speed), inducing loads higher than the certificated limit load).
Also, no information exists regarding damage tolerance on these
brackets to show the part can absorb any kind of crack without leading
to immediate failure.
Based on the above, the CASA and DCA both issued ADs for their
respective countries that require, before further flight, initial
inspections and, before the first flight of each day, repetitive
inspections.
The CTRM Aviation Sdn. Bhd. Model Eagle 150B airplane is the only
affected airplane model type certificated for operation in the United
States. There are currently 13 of these airplanes on the U.S. registry.
Based on all of this information from the State of Design, the FAA
issued AD 2004-11-04, Amendment 39-13649 (69 FR 30189, May 27, 2004).
AD 2004-11-04 currently requires that you do the following on CTRM
Aviation (formerly Eagle Aircraft (Malaysia) Sdn. Bhd.) Sdn. Bhd. Model
Eagle 150B airplanes:
Inspect certain canard inboard flap hinge support brackets
(initially before further flight and repetitively before the first
flight of each day); and;
Perform any necessary follow-up action.
The DCA recently notified FAA of the need to change AD 2004-11-04.
The DCA issued CAM AD 001-01-2004 R1, dated December 23, 2005. This
revision includes an optional modification as terminating action for
the repetitive inspections required by CAM AD 001-01-2004.
This condition, if not corrected, could result in loss of retention
of controls and, consequently, loss of airplane control.
Relevant Service Information
We have reviewed:
Eagle Aircraft Mandatory Service Bulletin SB 1109,
Revision Original, Effective Date August 29, 2003; and
Eagle Aircraft Mandatory Service Bulletin SB 1120,
Original, Effective Date June 3, 2005.
The service information describes procedures for:
Inspecting the gusset weld area of the canard inboard flap
hinge support brackets, part number (P/N) 5731D01-05 and P/N 5731D01-
02, for cracks; and;
Replacing any canard inboard flap hinge support brackets,
P/N 5731D01-05 and P/N 5731D01-02, with new design inboard flap hinge
brackets, P/N 5731D05-01 and P/N 5731D06-01.
Foreign Airworthiness Authority Information
The DCA classified these service bulletins as mandatory and issued
Malaysian AD No. CAM AD 001-01-2004 R1, dated December 23, 2005, to
ensure the continued airworthiness of these airplanes in Malaysia.
These CTRM Aviation Sdn. Bhd. Model Eagle 150B airplanes are
manufactured in Malaysia and are type-certificated for operation in the
United States under the provisions of section 21.29 of the Federal
Aviation Regulations (14 CFR 21.29) and the applicable bilateral
airworthiness agreement.
Under this bilateral airworthiness agreement, the DCA has kept us
informed of the situation described above.
FAA's Determination and Requirements of the Proposed AD
We are proposing this AD because we have examined the DCA's
findings, evaluated all information and determined the unsafe condition
described previously is likely to exist or develop on other products of
the same type design that are certificated for operation in the United
States.
This proposed AD would supersede AD 2004-11-04 with a new AD that
would initially retain the requirement that certain canard inboard flap
hinge support brackets be inspected (initially before further flight
and repetitively before the first flight of each day) and then require
that you replace the parts with new design inboard flap hinge brackets
as terminating action for the repetitive inspections or if cracks are
found. This proposed AD would require you to use the service
information described previously to perform these actions.
Costs of Compliance
We estimate that this proposed AD affects 13 airplanes in the U.S.
registry.
We estimate the following costs to do each proposed inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 = $80.................... (*) $80 13 x $80 = $1,040.
----------------------------------------------------------------------------------------------------------------
* Not applicable.
We estimate the following costs to do the replacements that would
be required as a result of the proposed inspection or the proposed
mandatory replacement:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
10 work-hours x $80 = $800................. $1,700 $2,500 13 x $2,500 = $32,500.
----------------------------------------------------------------------------------------------------------------
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
[[Page 39022]]
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information on
the Internet at https://dms.dot.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5227)
is located at the street address stated 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration 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 Airworthiness Directive
(AD) 2004-11-04, Amendment 39-13649 (69 FR 30189, May 27, 2004), and
adding the following new airworthiness directive:
CTRM Aviation SDN. BHD. (Formerly Eagle Aircraft (Malaysia) SDN.
BHD.): Docket No. FAA-2006-23786; Directorate Identifier 2006-CE-11-
AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this proposed airworthiness directive (AD) action by
August 10, 2006.
Affected ADs
(b) This AD supersedes AD 2004-11-04; Amendment 39-13649.
Applicability
(c) This AD affects Model Eagle 150B airplanes, all serial
numbers, that are certificated in any category.
Unsafe Condition
(d) This AD results from mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Malaysia. The actions specified in this AD are intended to detect
and correct cracks in the canard inboard flap hinge support
brackets, which could result in loss of retention of controls and
consequently, loss of airplane control.
Compliance
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspection gusset weld Initially inspect Follow Eagle
area of the canard inboard before the next Aircraft Mandatory
flap hinge support flight after June Service Bulletin SB
brackets, part number (P/N) 4, 2004 (the 1109, Revision
5731D01-05 and P/N 5731D01- effective date of Original, Effective
02, for cracked, lifted, or AD 2004-11-04). Date August 29,
missing paint in the area Repetitively 2003.
of the weld or suspected inspect thereafter
cracks. before the first
flight of each day.
(2) If cracked, lifted, or Before further Follow Eagle
missing paint in the area flight after any Aircraft Mandatory
of the weld or suspected inspection required Service Bulletin SB
cracks are found during any by paragraph (e)(1) 1109, Revision
inspection required in where cracked, Original, Effective
paragraph (e)(1) of this lifted, or missing Date August 29,
AD, inspect the affected paint in the area 2003.
bracket more fully as of the weld or
specified in the service suspected cracks
bulletin. are found.
(3) Replace any canard Before further Follow Eagle
inboard flap hinge support flight after any Aircraft Mandatory
brackets, P/N 5731D01-05 inspection where Service Bulletin SB
and P/N 5731D01-02, with cracks are found or 1120, Original,
new design inboard flap within 6 months Effective Date June
hinge brackets, P/N 5731D05- after the effective 3, 2005.
01 and P/N 5731D06-01. date of this AD,
whichever occurs
first. This action
terminates the
repetitive
inspections
required in
paragraph (e)(1) of
this AD.
(4) Do not install any As of the effective Not Applicable.
canard inboard flap hinge date of this AD.
support brackets, P/N
5731D01-05 and P/N 5731D01-
02.
------------------------------------------------------------------------
(f) The Australian AD allows an appropriately trained pilot to
perform the visual inspections of the canard inboard flap hinge
support brackets. Although the Malaysian AD does not specifically
state this, it does refer to the Australian AD. Regardless, the
Federal Aviation Regulations (14 CFR 43.3) only allow the pilot to
perform preventive maintenance as described in 14 CFR part 43, App.
A, paragraph (c). These visual inspections are not considered
preventive maintenance under 14 CFR part 43, App. A, paragraph (c).
Therefore, an appropriately-rated mechanic must perform all actions
of this AD.
Special Flight Permit
(g) Special flight permits are not allowed for this AD. Part 39
of the Federal Aviation Regulations (14 CFR part 39) provides that
FAA may issue special flight permits for ADs, unless otherwise
specified in the individual AD.s The FAA has determined
[[Page 39023]]
that the safety issue is severe enough that failure of the canard
inboard flap hinge support brackets must be prevented and cracks in
this area must be detected before further operation.
Alternative Methods of Compliance (AMOCs)
(h) The Manager, Standards Office, Small Airplane Directorate,
FAA, ATTN: Karl Schletzbaum, Aerospace Engineer, ACE-112, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: 816-329-4146; facsimile: 816-329-4090, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(i) AMOCs approved for AD 2004-11-04 are approved for this AD.
Related Information
(j) Malaysian AD No. CAM AD 001-01-2004 R1, dated December 23,
2005, and Australian AD No. CASA AD/X-TS/5, dated August 21, 2003,
revised April 2, 2004, also address the subject of this AD. To get
copies of the documents referenced in this AD, contact CTRM Aviation
Sdn. Bhd. (formerly known as Eagle Aircraft Sdn. Bhd.), Locked Bag
1028, Pejabat Pos Besar Melaka, 75150 Melaka, Malaysia; telephone:
06 317 1007; facsimile: 06 317 7023. To view the AD docket, go to
the Docket Management Facility; U.S. Department of Transportation,
400 Seventh Street, SW., Nassif Building, Room PL-401, Washington,
DC, or on the Internet at https://dms.dot.gov. The docket number is
Docket No. FAA-2006-23786; Directorate Identifier 2006-CE-11-AD.
Issued in Kansas City, Missouri, on July 3, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-10773 Filed 7-10-06; 8:45 am]
BILLING CODE 4910-13-P
