Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes, 66034-66038 [E9-29576]
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66034
Federal Register / Vol. 74, No. 238 / Monday, December 14, 2009 / Rules and Regulations
(c) Amount of penalty. The Director
may propose imposition of a civil
penalty for violation of a requirement of
a regulation under paragraph (a) of this
section or a compliance order issued
under paragraph (b) of this section, not
to exceed $150,000 for each violation.
*
*
*
*
*
PART 1050—FOREIGN GIFTS AND
DECORATIONS
27. The authority citation for part
1050 continues to read as follows:
■
Authority: The Constitution of the United
States, Article I, Section 9; 5 U.S.C. 7342; 22
U.S.C. 2694; 42 U.S.C. 7254 and 7262; 28
U.S.C. 2461 note.
28. Section 1050.303 is amended by
revising the last sentence in paragraph
(d) to read as follows:
■
§ 1050.303
Enforcement.
*
*
*
*
*
(d) * * * The court in which such
action is brought may assess a civil
penalty against such employee in any
amount not to exceed the retail value of
the gift improperly solicited or received
plus $8,000.
[FR Doc. E9–29667 Filed 12–11–09; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. FAA–2007–0083; Directorate
Identifier 2006–NM–266–AD; Amendment
39–16137; AD 2009–26–02]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135BJ,
–135ER, –135KE, –135KL, –135LR,
–145, –145ER, –145MR, –145LR,
–145XR, –145MP, and –145EP
Airplanes
srobinson on DSKHWCL6B1PROD with RULES
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
16:24 Dec 11, 2009
Jkt 220001
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
January 19, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 19, 2010.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1405; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a second supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that would apply to the specified
products. That second supplemental
NPRM was published in the Federal
Register on September 25, 2009 (74 FR
48877). That second supplemental
NPRM proposed to correct an unsafe
condition for the specified products.
The MCAI states:
Federal Aviation Administration
VerDate Nov<24>2008
It has been found the occurrence of engine
anti-ice system valve failure, where the valve
spring seat has broken and obstructed the
anti-ice system venturi tube. * * *
Therefore, should the aircraft encounter icing
conditions, ice may accrete in the engine
inlet lip and be ingested through the air inlet,
resulting in possible engine damage and
flame-out.
It has been found the occurrence of engine
anti-ice system valve failure, where the valve
spring seat has broken and obstructed the
anti-ice system venturi tube. Aircraft
dispatch with that failure may be allowed by
the operator Minimum Equipment List
(MEL), [if] the engine anti-ice system valve
[is] locked in the OPEN position. However,
there is no readily available means to make
sure the anti-ice system tubing is free of
debris, allowing unrestricted hot airflow to
the piccolo tube on the engine inlet lip.
Therefore, should the aircraft encounter icing
conditions, ice may accrete in the engine
inlet lip and be ingested through the air inlet,
resulting in possible engine damage and
flame-out.
The required actions include an
inspection to determine the part number
of the engine anti-icing system valves;
repetitive inspections of certain engine
anti-icing system valves and tubes to
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
detect damage, and replacement of the
valves if damage is found; and eventual
replacement of certain anti-icing system
valves. You may obtain further
information by examining the MCAI in
the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the second
supplemental NPRM or on the
determination of the cost to the public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a Note within the AD.
Costs of Compliance
We estimate that this AD will affect
697 products of U.S. registry. We also
estimate that it will take about 2 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $111,520, or $160 per product.
We also estimate that the replacement
specified in this AD will affect up to 306
parts. We estimate that it will take about
5 work-hours per part to comply with
the replacement requirements of this
AD. (Some airplanes have no affected
parts and other airplanes have either
one or two affected parts.) The cost of
each required part is $27,507. Where the
service information lists required parts
costs that are covered under warranty,
we have assumed that there will be no
charge for these costs. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of the
replacement specified in the AD on U.S.
operators to be $8,539,542, or $27,907
per part.
E:\FR\FM\14DER1.SGM
14DER1
Federal Register / Vol. 74, No. 238 / Monday, December 14, 2009 / Rules and Regulations
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
srobinson on DSKHWCL6B1PROD with RULES
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
VerDate Nov<24>2008
16:24 Dec 11, 2009
Jkt 220001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2009–26–02 Empresa Brasileira de
Aeronautica S.A. (EMBRAER):
Amendment 39–16137. Docket No.
FAA–2007–0083; Directorate Identifier
2006–NM–266–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 19, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to EMBRAER Model
EMB–135BJ, –135ER, –135KE, –135KL,
–135LR, –145, –145ER, –145MR, –145LR,
–145XR, –145MP, and –145EP airplanes,
certificated in any category, except airplanes
having serial numbers 14500921, 14500928,
14500932, 14500949, 14500958, 14500971,
14500973 and up, which will have in-factory
modification incorporated.
Subject
(d) Air Transport Association of America
Code 30: Ice and Rain Protection.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
It has been found the occurrence of engine
anti-ice system valve failure, where the valve
spring seat has broken and obstructed the
anti-ice system venturi tube. Aircraft
dispatch with that failure may be allowed by
the operator Minimum Equipment List
(MEL), [if] the engine anti-ice system valve
[is] locked in the OPEN position. However,
there is no readily available means to make
sure the anti-ice system tubing is free of
debris, allowing unrestricted hot airflow to
the piccolo tube on the engine inlet lip.
Therefore, should the aircraft encounter icing
conditions, ice may accrete in the engine
inlet lip and be ingested through the air inlet,
resulting in possible engine damage and
flame-out.
The required actions include an inspection to
determine the part number of the engine antiicing system valves; repetitive inspections of
certain engine anti-icing system valves and
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
66035
tubes to detect damage, and replacement of
the valves if damage is found; and eventual
replacement of certain anti-icing system
valves.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) PART I—Within 500 flight hours or 3
months after the effective date of this AD,
whichever occurs first, carry out a general
visual inspection of both LH (left-hand) and
RH (right-hand) engine anti-ice system valves
to determine their P/N (part number).
(i) For engine anti-ice system valves with
P/N C146009–2: No further action is required
by paragraph (f)(1) of this AD.
(ii) For engine anti-ice system valves with
P/N C146009–3: Before further flight, remove
the valve and carry out a detailed inspection
regarding its integrity; and carry out a special
detailed inspection for an obstruction in the
corresponding engine anti-ice system tubes;
according to the detailed instructions and
procedures described in Embraer Service
Bulletin 145–30–0049, dated June 28, 2006,
or Revision 01, dated October 19, 2006; or
Embraer Service Bulletin 145LEG–30–0016,
dated June 28, 2006, or Revision 01, dated
February 5, 2007; as applicable.
(A) If the valve is damaged or the tube is
obstructed, before further flight: Replace the
valve with a serviceable or new valve bearing
P/N C146009–2, C146009–3, or C146009–4;
or remove all obstructions; as applicable; in
accordance with the Accomplishment
Instructions of Embraer Service Bulletin 145–
30–0049, dated June 28, 2006, or Revision 01,
dated October 19, 2006; or Embraer Service
Bulletin 145LEG–30–0016, dated June 28,
2006, or Revision 01, dated February 5, 2007;
as applicable.
(B) If the valve is not damaged or the tube
is not obstructed, re-install the valve or
install a serviceable or new valve bearing
P/N C146009–2, C146009–3, or C146009–4;
or re-install the tube; in accordance with the
Accomplishment Instructions of Embraer
Service Bulletin 145–30–0049, dated June 28,
2006, or Revision 01, dated October 19, 2006;
or Embraer Service Bulletin 145LEG–30–
0016, dated June 28, 2006, or Revision 01,
dated February 5, 2007; as applicable.
(iii) For engine anti-ice system valves with
P/N C146009–4: No further action is required
by paragraph (f)(1) of this AD. In this case,
paragraphs (f)(2), (f)(3), (f)(4), (f)(7), and (f)(8)
of this AD are not applicable. However,
paragraphs (f)(5) and (f)(6) of this AD must
be accomplished.
(2) PART II—Within 1,500 flight hours or
9 months after the effective date of this AD,
whichever occurs first, and thereafter at
intervals that do not exceed 1,000 flight
hours or 6 months, whichever occurs first,
carry out a detailed inspection for damage of
both LH and RH engine anti-ice system
valves bearing P/N C146009–2 or C146009–
3; and a special detailed inspection for
obstruction of the corresponding engine antiice system tubes; according to the detailed
instructions and procedures described in
Embraer Service Bulletin 145–30–0049, dated
June 28, 2006, or Revision 01, dated October
19, 2006; or Embraer Service Bulletin
145LEG–30–0016, dated June 28, 2006, or
E:\FR\FM\14DER1.SGM
14DER1
srobinson on DSKHWCL6B1PROD with RULES
66036
Federal Register / Vol. 74, No. 238 / Monday, December 14, 2009 / Rules and Regulations
Revision 01, dated February 5, 2007; as
applicable; and accomplish paragraphs
(f)(2)(i) and (f)(2)(ii) of this AD, as applicable.
(i) If the valve is damaged or the tube is
obstructed, before further flight: Replace the
valve with a serviceable or new valve bearing
P/N C146009–2, C146009–3, or C146009–4;
or remove all obstructions; as applicable; in
accordance with the Accomplishment
Instructions of Embraer Service Bulletin 145–
30–0049, dated June 28, 2006, or Revision 01,
dated October 19, 2006; or Embraer Service
Bulletin 145LEG–30–0016, dated June 28,
2006, or Revision 01, dated February 5, 2007;
as applicable.
(ii) If the valve is not damaged, or the tube
is not obstructed, before further flight: Reinstall the valve or install a serviceable or
new valve bearing P/N C146009–2 C146009–
3, or C146009–4; or re-install the tube; as
applicable; in accordance with the
Accomplishment Instructions of Embraer
Service Bulletin 145–30–0049, dated June 28,
2006, or Revision 01, dated October 19, 2006;
or Embraer Service Bulletin 145LEG–30–
0016, dated June 28, 2006, or Revision 01,
dated February 5, 2007; as applicable.
(3) PART III—Any engine anti-ice system
valve with P/N C146009–2 or C146009–3 that
will be installed as a replacement, as
provided for in paragraphs (f)(1) and (f)(2) of
this AD, must undergo a detailed inspection
for its integrity before installation, according
to the detailed instructions and procedures
described in Embraer Service Bulletin 145–
30–0049, dated June 28, 2006, or Revision 01,
dated October 19, 2006; or Embraer Service
Bulletin 145LEG–30–0016, dated June 28,
2006, or Revision 01, dated February 5, 2007;
as applicable; and additionally adhere to
paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, as
applicable.
(i) If the valve is damaged, replace it with
a serviceable or new valve bearing P/N
C146009–2, C146009–3, or C146009–4; in
accordance with the Accomplishment
Instructions of Embraer Service Bulletin 145–
30–0049, dated June 28, 2006, or Revision 01,
dated October 19, 2006; or Embraer Service
Bulletin 145LEG–30–0016, dated June 28,
2006, or Revision 01, dated February 5, 2007;
as applicable.
(ii) If the valve is not damaged, installation
is permitted.
(4) PART IV—Any engine anti-ice system
tubes that will be installed on the airplane as
a replacement, as provided for in paragraphs
(f)(1) and (f)(2) of this AD, must undergo a
special detailed inspection before
installation, and all obstructions removed,
according to the detailed instructions and
procedures described in Embraer Service
Bulletin 145–30–0049, dated June 28, 2006,
or Revision 01, dated October 19, 2006; or
Embraer Service Bulletin 145LEG–30–0016,
dated June 28, 2006, or Revision 01, dated
February 5, 2007; as applicable.
(5) PART V—If any engine anti-ice system
valve with P/N C146009–4 has been found
during the inspection required by paragraph
(f)(1) of this AD, do paragraphs (f)(5)(i) or
(f)(5)(ii) of this AD, as applicable, within 500
flight hours or 6 months after the effective
date of this AD, whichever occurs first.
(i) If the valve was installed according to
the detailed instructions and procedures
VerDate Nov<24>2008
16:24 Dec 11, 2009
Jkt 220001
described in Embraer Service Bulletin 145–
30–0044, Revision 01, dated June 26, 2006,
Revision 02, dated September 25, 2006,
Revision 03, dated December 12, 2006, or
Revision 04, dated May 14, 2008; or Embraer
Service Bulletin 145LEG–30–0018, Revision
02, dated December 12, 2006, or Revision 03,
dated May 14, 2008; as applicable: No further
action is required by this AD.
(ii) If the valve was installed according to
detailed instructions and procedures other
than those specified in paragraph (f)(5)(i) of
this AD: Carry out a special detailed
inspection in the corresponding engine antiice system tubes, and repair all damage and
remove all obstructions; according to the
detailed instructions and procedures
described in Embraer Service Bulletin 145–
30–0049, dated June 28, 2006, or Revision 01,
dated October 19, 2006; or Embraer Service
Bulletin 145LEG–30–0016, dated June 28,
2006, or Revision 01, dated February 5, 2007;
as applicable. After doing the actions
specified in paragraph (f)(5)(ii) of this AD, no
further action is required by this AD.
(6) PART VI—Before aircraft dispatch with
one or two engine anti-ice system valves
inoperative (Master Minimum Equipment
List (MMEL) 30–21–01), carry out a detailed
inspection for damage of the affected engine
anti-ice system valves; and a special detailed
inspection for obstruction of the
corresponding engine anti-ice system tubes;
and replace all damaged valves and remove
all obstructions before further flight. Do all
actions according to the detailed instructions
and procedures described in Embraer Service
Bulletin 145–30–0049, dated June 28, 2006,
or Revision 01, dated October 19, 2006; or
Embraer Service Bulletin 145LEG–30–0016,
dated June 28, 2006, or Revision 01, dated
February 5, 2007; as applicable; by
accomplishing paragraph (f)(2) of this AD,
unless the condition specified in paragraph
(f)(6)(i) or (f)(6)(ii) of this AD has been met.
(i) Valves with P/N C146009–4 have been
previously installed according to the detailed
instructions and procedures described in
Embraer Service Bulletin 145–30–0044, dated
October 31, 2005; Embraer Service Bulletin
145LEG–30–0018, dated June 26, 2006; or
Embraer Service Bulletin 145LEG–30–0018,
Revision 01, dated September 25, 2006; as
applicable; and additionally, paragraph
(f)(5)(ii) of this AD has been accomplished.
(ii) Valves with P/N C146009–4 have been
previously installed according to the detailed
instructions and procedures described in
Embraer Service Bulletin 145–30–0044,
Revision 01, dated June 26, 2006, Revision
02, dated September 25, 2006, Revision 03,
dated December 12, 2006, or Revision 04,
dated May 14, 2008; or Embraer Service
Bulletin 145LEG–30–0018, Revision 02,
dated December 12, 2006, or Revision 03,
dated May 14, 2008; as applicable.
(7) PART VII—Within 1,000 flight hours or
10 months after the effective date of this AD,
whichever occurs first, install engine anti-ice
system valves bearing P/N C146009–4 in the
LH and RH engine positions, replacing P/N
C146009–3, according to the detailed
instructions and procedures described in
Embraer Service Bulletin 145–30–0044,
Revision 01, dated June 26, 2006, Revision
02, dated September 25, 2006, Revision 03,
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
dated December 12, 2006, or Revision 04,
dated May 14, 2008; or Embraer Service
Bulletin 145LEG–30–0018, Revision 02,
dated December 12, 2006, or Revision 03,
dated May 14, 2008; as applicable.
(8) PART VIII—Within 1,000 flight hours
or 10 months after the effective date of this
AD, whichever occurs first, install engine
anti-ice system valves bearing P/N C146009–
4 in the LH and RH engine positions,
replacing P/N C146009–2, according to the
detailed instructions and procedures
described in Embraer Service Bulletin 145–
30–0044, Revision 01, dated June 26, 2006;
Revision 02, dated September 25, 2006,
Revision 03, dated December 12, 2006, or
Revision 04, dated May 14, 2008; or Embraer
Service Bulletin 145LEG–30–0018, Revision
02, dated December 12, 2006, or Revision 03,
dated May 14, 2008; as applicable.
(9) PART IX—The installation of engine
anti-ice system valves bearing P/N C146009–
4 according to the detailed instructions and
procedures described in Embraer Service
Bulletin 145–30–0044, Revision 01, dated
June 26, 2006, Revision 02, dated September
25, 2006, Revision 03, dated December 12,
2006; or Revision 04, dated May 14, 2008; or
Embraer Service Bulletin 145LEG–30–0018,
Revision 02, dated December 12, 2006, or
Revision 03, dated May 14, 2008; as
applicable; constitutes terminating action for
this AD.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
Note 2: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Note 3: For the purposes of this AD, a
special detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. The examination is likely to
make extensive use of specialized inspection
techniques and/or equipment. Intricate
cleaning and substantial access or
disassembly procedure may be required.’’
FAA AD Differences
Note 4: This AD differs from the MCAI
and/or service information as follows (we
have coordinated these differences with
ˆ
Agencia Nacional de Aviacao Civil (ANAC)):
¸˜
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Federal Register / Vol. 74, No. 238 / Monday, December 14, 2009 / Rules and Regulations
(1) ‘‘Part V’’ of the MCAI specifies a
compliance time of within ‘‘1,500 flight
hours or 9 months.’’ However, paragraph
(f)(5) of this AD requires compliance ‘‘within
500 flight hours or 6 months’’ for the
corresponding action.
(2) ‘‘Part VII’’ of the MCAI specifies a
compliance time of ‘‘within 2,500 flight
hours or 12 months.’’ However, paragraph
(f)(7) of this AD requires compliance ‘‘within
1,000 flight hours or 10 months’’ for the
corresponding action.
(3) ‘‘Part VIII’’ of the MCAI specifies a
compliance time of ‘‘within 6,000 flight
hours or 30 months.’’ However, paragraph
(f)(8) of this AD requires compliance ‘‘within
1,000 flight hours or 10 months’’ for the
corresponding action.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, ANM–116,
International Branch, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Sanjay Ralhan,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1405; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(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
66037
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to Brazilian Airworthiness
Directive 2006–09–03R1, effective January 4,
2007; and the service bulletins listed in Table
1 of this AD; for related information.
TABLE 1—RELATED SERVICE BULLETINS
Embraer Service Bulletin—
Revision—
Dated—
145–30–0044 ....................................................................
145–30–0044 ....................................................................
145–30–0044 ....................................................................
145–30–0044 ....................................................................
145–30–0049 ....................................................................
145–30–0049 ....................................................................
145LEG–30–0016 .............................................................
145LEG–30–0016 .............................................................
145LEG–30–0018 .............................................................
145LEG–30–0018 .............................................................
01 ....................................................................................
02 ....................................................................................
03 ....................................................................................
04 ....................................................................................
Original ............................................................................
01 ....................................................................................
Original ............................................................................
01 ....................................................................................
02 ....................................................................................
03 ....................................................................................
June 26, 2006.
September 25, 2006.
December 12, 2006.
May 14, 2008.
June 28, 2006.
October 19, 2006.
June 28, 2006.
February 5, 2007.
December 12, 2006.
May 14, 2008
Material Incorporated by Reference
(i) You must use the applicable service
information contained in Table 2 of this AD
to do the actions required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Empresa Brasileira de
Aeronautica S.A. (EMBRAER), Technical
Publications Section (PC 060), Av. Brigadeiro
˜
Faria Lima, 2170—Putim—12227–901 Sao
Jose dos Campos—SP—BRASIL; telephone:
+55 12 3927–5852 or +55 12 3309–0732; fax:
+55 12 3927–7546; e-mail:
distrib@embraer.com.br; Internet: https://
www.flyembraer.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
TABLE 2—MATERIAL INCORPORATED BY REFERENCE
Revision—
Dated—
145LEG–30–0016 .............................................................
145LEG–30–0016 .............................................................
145LEG–30–0018 .............................................................
145LEG–30–0018 .............................................................
145–30–0044 ....................................................................
145–30–0044 ....................................................................
145–30–0044 ....................................................................
145–30–0044 ....................................................................
145–30–0049 ....................................................................
145–30–0049 ....................................................................
srobinson on DSKHWCL6B1PROD with RULES
Embraer Service Bulletin—
Original ............................................................................
01 ....................................................................................
02 ....................................................................................
03 ....................................................................................
01 ....................................................................................
02 ....................................................................................
03 ....................................................................................
04 ....................................................................................
Original ............................................................................
01 ....................................................................................
June 28, 2006.
February 5, 2007.
December 12, 2006.
May 14, 2008.
June 26, 2006.
September 25, 2006.
December 12, 2006.
May 14, 2008.
June 28, 2006.
October 19, 2006.
VerDate Nov<24>2008
16:24 Dec 11, 2009
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Frm 00009
Fmt 4700
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E:\FR\FM\14DER1.SGM
14DER1
66038
Federal Register / Vol. 74, No. 238 / Monday, December 14, 2009 / Rules and Regulations
Issued in Renton, Washington, on
December 1, 2009.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–29576 Filed 12–11–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1008; Directorate
Identifier 2008–SW–62–AD; Amendment 39–
16063; AD 2009–22–10]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France (ECF) Model AS332C, AS332L,
AS332L1, AS332L2, SA330F, SA330G,
and SA330J Helicopters
srobinson on DSKHWCL6B1PROD with RULES
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
specified ECF helicopters. This AD
results from a mandatory continuing
airworthiness information (MCAI) AD
issued by the European Aviation Safety
Agency (EASA), the Technical Agent for
the aviation authority of France. The
MCAI AD states there have been two
cases of failure of the screw that secures
the main rotor blade (blade) deicing
system distributor retaining clamp
(clamp). Analysis revealed that these
failures were the result of insufficient
clearance of the screw and the clamp
assembly causing the screw to bend and
also by some screws having
nonconforming material hardness. Also,
some of the screw heads were missing
a lock-wiring hole preventing the use of
lock-wiring between the screw head and
the nut.
These actions are intended to detect
failure of the clamp attachment screw
leading to damage to the main or tail
rotor blades and risk to persons on the
ground by impact from a departed screw
or clamp.
DATES: This AD becomes effective on
December 29, 2009.
The incorporation by reference of
certain publications is approved by the
Director of the Federal Register as of
December 29, 2009.
We must receive comments by
February 12, 2010.
ADDRESSES: You may send comments by
any of the following methods:
VerDate Nov<24>2008
16:24 Dec 11, 2009
Jkt 220001
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting 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: 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.
You may get the service information
identified in this AD from American
Eurocopter Corporation, 2701 Forum
Drive, Grand Prairie, TX 75053–4005,
telephone (800) 232–0323, fax (972)
641–3710, or at https://
www.eurocopter.com.
Examining the 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 AD, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is
stated in the ADDRESSES section of this
AD. Comments will be available in the
AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
DOT/FAA Southwest Region, J.R.
Holton, Jr., ASW–112, Aviation Safety
Engineer, Rotorcraft Directorate, Safety
Management Group, 2601 Meacham
Blvd., Fort Worth, Texas 76137,
telephone (817) 222–4964, fax (817)
222–5961.
SUPPLEMENTARY INFORMATION:
some cases, the screw head was missing
a lock-wiring hole making it impossible
to install a safety-wire between the
screw head and the nut. Failure of the
clamp attachment screw can lead to
damage to the main or tail rotor blades
and is a risk for persons on the ground.
You may obtain further information
by examining the DGAC and MCAI ADs
and any related service information in
the AD docket.
Discussion
Differences Between This AD and the
MCAI AD
EASA, which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD 2009–
0003R1, dated January 13, 2009, to
correct an unsafe condition for the
specified Eurocopter model helicopters.
That EASA AD superseded EASA AD
2009–003–E, dated January 6, 2009,
which superseded EASA AD 2008–
0162–E, dated August 26, 2008, which
´ ´
superseded Direction generale de
l’aviation civile (DGAC) AD UF–2008–
029, dated August 21, 2008.
EASA reports two cases of failure of
the screw that secures the blade clamp.
Analyses revealed that these failures of
the screw were the result of assembly
stress in the screw head and
nonconforming screw hardness. Also, in
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
Related Service Information
Eurocopter has issued Emergency
Alert Service Bulletin (ASB) No.
30.00.66 for the Model AS332C, C1, L,
and L1; and No. 30.20 for the Model
SA330J, F, and G, both Revision 1 and
both dated August 21, 2008. The ASBs
specify removing the retaining clamp
from the distributor, checking the blade
clamp and attachment screw for
interference between the screw head
and the clamp, checking for a crack in
the shank of the screw, checking for a
lock-wiring hole in the screw, and
identifying the clamp with a ‘‘V.’’ The
actions described in the EASA MCAI
AD are intended to correct the same
unsafe condition as that identified in
the service information.
FAA’s Evaluation and Unsafe Condition
Determination
These helicopters have been approved
by the aviation authority of France, and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, EASA, the
Technical Agent for France, has notified
us of the unsafe condition described in
the EASA MCAI AD. We are issuing this
AD because we evaluated all
information provided by the EASA and
determined the unsafe condition exists
and is likely to exist or develop on other
helicopters of these same type designs.
We describe the action taken in the
AD as an inspection rather than a check.
Costs of Compliance
We estimate that this AD will affect
about 16 helicopters of U.S. registry. We
also estimate that it will take about 3
work-hours per helicopter to inspect the
blade clamp and attachment screw and
replace the screw on each helicopter.
The average labor rate is $80 per workhour. Required parts will cost about
$200 per helicopter. Based on these
figures, we estimate the cost of this AD
on U.S. operators will be $7,040,
assuming the clamp and attachment
screw are replaced on each helicopter.
E:\FR\FM\14DER1.SGM
14DER1
]]>Agencies
[Federal Register Volume 74, Number 238 (Monday, December 14, 2009)]
[Rules and Regulations]
[Pages 66034-66038]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-29576]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0083; Directorate Identifier 2006-NM-266-AD;
Amendment 39-16137; AD 2009-26-02]
RIN 2120-AA64
Airworthiness Directives; Empresa Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, -145, -
145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
It has been found the occurrence of engine anti-ice system valve
failure, where the valve spring seat has broken and obstructed the
anti-ice system venturi tube. * * * Therefore, should the aircraft
encounter icing conditions, ice may accrete in the engine inlet lip
and be ingested through the air inlet, resulting in possible engine
damage and flame-out.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective January 19, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 19,
2010.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1405; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a second supplemental notice of proposed rulemaking
(NPRM) to amend 14 CFR part 39 to include an AD that would apply to the
specified products. That second supplemental NPRM was published in the
Federal Register on September 25, 2009 (74 FR 48877). That second
supplemental NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
It has been found the occurrence of engine anti-ice system valve
failure, where the valve spring seat has broken and obstructed the
anti-ice system venturi tube. Aircraft dispatch with that failure
may be allowed by the operator Minimum Equipment List (MEL), [if]
the engine anti-ice system valve [is] locked in the OPEN position.
However, there is no readily available means to make sure the anti-
ice system tubing is free of debris, allowing unrestricted hot
airflow to the piccolo tube on the engine inlet lip. Therefore,
should the aircraft encounter icing conditions, ice may accrete in
the engine inlet lip and be ingested through the air inlet,
resulting in possible engine damage and flame-out.
The required actions include an inspection to determine the part number
of the engine anti-icing system valves; repetitive inspections of
certain engine anti-icing system valves and tubes to detect damage, and
replacement of the valves if damage is found; and eventual replacement
of certain anti-icing system valves. You may obtain further information
by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the second supplemental NPRM or on
the determination of the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a Note within the AD.
Costs of Compliance
We estimate that this AD will affect 697 products of U.S. registry.
We also estimate that it will take about 2 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $80 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $111,520, or $160 per product.
We also estimate that the replacement specified in this AD will
affect up to 306 parts. We estimate that it will take about 5 work-
hours per part to comply with the replacement requirements of this AD.
(Some airplanes have no affected parts and other airplanes have either
one or two affected parts.) The cost of each required part is $27,507.
Where the service information lists required parts costs that are
covered under warranty, we have assumed that there will be no charge
for these costs. As we do not control warranty coverage for affected
parties, some parties may incur costs higher than estimated here. Based
on these figures, we estimate the cost of the replacement specified in
the AD on U.S. operators to be $8,539,542, or $27,907 per part.
[[Page 66035]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2009-26-02 Empresa Brasileira de Aeronautica S.A. (EMBRAER):
Amendment 39-16137. Docket No. FAA-2007-0083; Directorate Identifier
2006-NM-266-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
19, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to EMBRAER Model EMB-135BJ, -135ER, -135KE,
-135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -
145EP airplanes, certificated in any category, except airplanes
having serial numbers 14500921, 14500928, 14500932, 14500949,
14500958, 14500971, 14500973 and up, which will have in-factory
modification incorporated.
Subject
(d) Air Transport Association of America Code 30: Ice and Rain
Protection.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
It has been found the occurrence of engine anti-ice system valve
failure, where the valve spring seat has broken and obstructed the
anti-ice system venturi tube. Aircraft dispatch with that failure
may be allowed by the operator Minimum Equipment List (MEL), [if]
the engine anti-ice system valve [is] locked in the OPEN position.
However, there is no readily available means to make sure the anti-
ice system tubing is free of debris, allowing unrestricted hot
airflow to the piccolo tube on the engine inlet lip. Therefore,
should the aircraft encounter icing conditions, ice may accrete in
the engine inlet lip and be ingested through the air inlet,
resulting in possible engine damage and flame-out.
The required actions include an inspection to determine the part
number of the engine anti-icing system valves; repetitive
inspections of certain engine anti-icing system valves and tubes to
detect damage, and replacement of the valves if damage is found; and
eventual replacement of certain anti-icing system valves.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) PART I--Within 500 flight hours or 3 months after the
effective date of this AD, whichever occurs first, carry out a
general visual inspection of both LH (left-hand) and RH (right-hand)
engine anti-ice system valves to determine their P/N (part number).
(i) For engine anti-ice system valves with P/N C146009-2: No
further action is required by paragraph (f)(1) of this AD.
(ii) For engine anti-ice system valves with P/N C146009-3:
Before further flight, remove the valve and carry out a detailed
inspection regarding its integrity; and carry out a special detailed
inspection for an obstruction in the corresponding engine anti-ice
system tubes; according to the detailed instructions and procedures
described in Embraer Service Bulletin 145-30-0049, dated June 28,
2006, or Revision 01, dated October 19, 2006; or Embraer Service
Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated
February 5, 2007; as applicable.
(A) If the valve is damaged or the tube is obstructed, before
further flight: Replace the valve with a serviceable or new valve
bearing P/N C146009-2, C146009-3, or C146009-4; or remove all
obstructions; as applicable; in accordance with the Accomplishment
Instructions of Embraer Service Bulletin 145-30-0049, dated June 28,
2006, or Revision 01, dated October 19, 2006; or Embraer Service
Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated
February 5, 2007; as applicable.
(B) If the valve is not damaged or the tube is not obstructed,
re-install the valve or install a serviceable or new valve bearing
P/N C146009-2, C146009-3, or C146009-4; or re-install the tube; in
accordance with the Accomplishment Instructions of Embraer Service
Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated
October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated
June 28, 2006, or Revision 01, dated February 5, 2007; as
applicable.
(iii) For engine anti-ice system valves with P/N C146009-4: No
further action is required by paragraph (f)(1) of this AD. In this
case, paragraphs (f)(2), (f)(3), (f)(4), (f)(7), and (f)(8) of this
AD are not applicable. However, paragraphs (f)(5) and (f)(6) of this
AD must be accomplished.
(2) PART II--Within 1,500 flight hours or 9 months after the
effective date of this AD, whichever occurs first, and thereafter at
intervals that do not exceed 1,000 flight hours or 6 months,
whichever occurs first, carry out a detailed inspection for damage
of both LH and RH engine anti-ice system valves bearing P/N C146009-
2 or C146009-3; and a special detailed inspection for obstruction of
the corresponding engine anti-ice system tubes; according to the
detailed instructions and procedures described in Embraer Service
Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated
October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated
June 28, 2006, or
[[Page 66036]]
Revision 01, dated February 5, 2007; as applicable; and accomplish
paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, as applicable.
(i) If the valve is damaged or the tube is obstructed, before
further flight: Replace the valve with a serviceable or new valve
bearing P/N C146009-2, C146009-3, or C146009-4; or remove all
obstructions; as applicable; in accordance with the Accomplishment
Instructions of Embraer Service Bulletin 145-30-0049, dated June 28,
2006, or Revision 01, dated October 19, 2006; or Embraer Service
Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated
February 5, 2007; as applicable.
(ii) If the valve is not damaged, or the tube is not obstructed,
before further flight: Re-install the valve or install a serviceable
or new valve bearing P/N C146009-2 C146009-3, or C146009-4; or re-
install the tube; as applicable; in accordance with the
Accomplishment Instructions of Embraer Service Bulletin 145-30-0049,
dated June 28, 2006, or Revision 01, dated October 19, 2006; or
Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or
Revision 01, dated February 5, 2007; as applicable.
(3) PART III--Any engine anti-ice system valve with P/N C146009-
2 or C146009-3 that will be installed as a replacement, as provided
for in paragraphs (f)(1) and (f)(2) of this AD, must undergo a
detailed inspection for its integrity before installation, according
to the detailed instructions and procedures described in Embraer
Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01,
dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016,
dated June 28, 2006, or Revision 01, dated February 5, 2007; as
applicable; and additionally adhere to paragraphs (f)(3)(i) and
(f)(3)(ii) of this AD, as applicable.
(i) If the valve is damaged, replace it with a serviceable or
new valve bearing P/N C146009-2, C146009-3, or C146009-4; in
accordance with the Accomplishment Instructions of Embraer Service
Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated
October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated
June 28, 2006, or Revision 01, dated February 5, 2007; as
applicable.
(ii) If the valve is not damaged, installation is permitted.
(4) PART IV--Any engine anti-ice system tubes that will be
installed on the airplane as a replacement, as provided for in
paragraphs (f)(1) and (f)(2) of this AD, must undergo a special
detailed inspection before installation, and all obstructions
removed, according to the detailed instructions and procedures
described in Embraer Service Bulletin 145-30-0049, dated June 28,
2006, or Revision 01, dated October 19, 2006; or Embraer Service
Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated
February 5, 2007; as applicable.
(5) PART V--If any engine anti-ice system valve with P/N
C146009-4 has been found during the inspection required by paragraph
(f)(1) of this AD, do paragraphs (f)(5)(i) or (f)(5)(ii) of this AD,
as applicable, within 500 flight hours or 6 months after the
effective date of this AD, whichever occurs first.
(i) If the valve was installed according to the detailed
instructions and procedures described in Embraer Service Bulletin
145-30-0044, Revision 01, dated June 26, 2006, Revision 02, dated
September 25, 2006, Revision 03, dated December 12, 2006, or
Revision 04, dated May 14, 2008; or Embraer Service Bulletin 145LEG-
30-0018, Revision 02, dated December 12, 2006, or Revision 03, dated
May 14, 2008; as applicable: No further action is required by this
AD.
(ii) If the valve was installed according to detailed
instructions and procedures other than those specified in paragraph
(f)(5)(i) of this AD: Carry out a special detailed inspection in the
corresponding engine anti-ice system tubes, and repair all damage
and remove all obstructions; according to the detailed instructions
and procedures described in Embraer Service Bulletin 145-30-0049,
dated June 28, 2006, or Revision 01, dated October 19, 2006; or
Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or
Revision 01, dated February 5, 2007; as applicable. After doing the
actions specified in paragraph (f)(5)(ii) of this AD, no further
action is required by this AD.
(6) PART VI--Before aircraft dispatch with one or two engine
anti-ice system valves inoperative (Master Minimum Equipment List
(MMEL) 30-21-01), carry out a detailed inspection for damage of the
affected engine anti-ice system valves; and a special detailed
inspection for obstruction of the corresponding engine anti-ice
system tubes; and replace all damaged valves and remove all
obstructions before further flight. Do all actions according to the
detailed instructions and procedures described in Embraer Service
Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated
October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated
June 28, 2006, or Revision 01, dated February 5, 2007; as
applicable; by accomplishing paragraph (f)(2) of this AD, unless the
condition specified in paragraph (f)(6)(i) or (f)(6)(ii) of this AD
has been met.
(i) Valves with P/N C146009-4 have been previously installed
according to the detailed instructions and procedures described in
Embraer Service Bulletin 145-30-0044, dated October 31, 2005;
Embraer Service Bulletin 145LEG-30-0018, dated June 26, 2006; or
Embraer Service Bulletin 145LEG-30-0018, Revision 01, dated
September 25, 2006; as applicable; and additionally, paragraph
(f)(5)(ii) of this AD has been accomplished.
(ii) Valves with P/N C146009-4 have been previously installed
according to the detailed instructions and procedures described in
Embraer Service Bulletin 145-30-0044, Revision 01, dated June 26,
2006, Revision 02, dated September 25, 2006, Revision 03, dated
December 12, 2006, or Revision 04, dated May 14, 2008; or Embraer
Service Bulletin 145LEG-30-0018, Revision 02, dated December 12,
2006, or Revision 03, dated May 14, 2008; as applicable.
(7) PART VII--Within 1,000 flight hours or 10 months after the
effective date of this AD, whichever occurs first, install engine
anti-ice system valves bearing P/N C146009-4 in the LH and RH engine
positions, replacing P/N C146009-3, according to the detailed
instructions and procedures described in Embraer Service Bulletin
145-30-0044, Revision 01, dated June 26, 2006, Revision 02, dated
September 25, 2006, Revision 03, dated December 12, 2006, or
Revision 04, dated May 14, 2008; or Embraer Service Bulletin 145LEG-
30-0018, Revision 02, dated December 12, 2006, or Revision 03, dated
May 14, 2008; as applicable.
(8) PART VIII--Within 1,000 flight hours or 10 months after the
effective date of this AD, whichever occurs first, install engine
anti-ice system valves bearing P/N C146009-4 in the LH and RH engine
positions, replacing P/N C146009-2, according to the detailed
instructions and procedures described in Embraer Service Bulletin
145-30-0044, Revision 01, dated June 26, 2006; Revision 02, dated
September 25, 2006, Revision 03, dated December 12, 2006, or
Revision 04, dated May 14, 2008; or Embraer Service Bulletin 145LEG-
30-0018, Revision 02, dated December 12, 2006, or Revision 03, dated
May 14, 2008; as applicable.
(9) PART IX--The installation of engine anti-ice system valves
bearing P/N C146009-4 according to the detailed instructions and
procedures described in Embraer Service Bulletin 145-30-0044,
Revision 01, dated June 26, 2006, Revision 02, dated September 25,
2006, Revision 03, dated December 12, 2006; or Revision 04, dated
May 14, 2008; or Embraer Service Bulletin 145LEG-30-0018, Revision
02, dated December 12, 2006, or Revision 03, dated May 14, 2008; as
applicable; constitutes terminating action for this AD.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
Note 2: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Note 3: For the purposes of this AD, a special detailed
inspection is: ``An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or
irregularity. The examination is likely to make extensive use of
specialized inspection techniques and/or equipment. Intricate
cleaning and substantial access or disassembly procedure may be
required.''
FAA AD Differences
Note 4: This AD differs from the MCAI and/or service information
as follows (we have coordinated these differences with Ag[ecirc]ncia
Nacional de Avia[ccedil][atilde]o Civil (ANAC)):
[[Page 66037]]
(1) ``Part V'' of the MCAI specifies a compliance time of within
``1,500 flight hours or 9 months.'' However, paragraph (f)(5) of
this AD requires compliance ``within 500 flight hours or 6 months''
for the corresponding action.
(2) ``Part VII'' of the MCAI specifies a compliance time of
``within 2,500 flight hours or 12 months.'' However, paragraph
(f)(7) of this AD requires compliance ``within 1,000 flight hours or
10 months'' for the corresponding action.
(3) ``Part VIII'' of the MCAI specifies a compliance time of
``within 6,000 flight hours or 30 months.'' However, paragraph
(f)(8) of this AD requires compliance ``within 1,000 flight hours or
10 months'' for the corresponding action.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, International Branch, Transport Airplane Directorate, FAA, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-1405; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards District Office.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to Brazilian Airworthiness Directive 2006-09-03R1,
effective January 4, 2007; and the service bulletins listed in Table
1 of this AD; for related information.
Table 1--Related Service Bulletins
----------------------------------------------------------------------------------------------------------------
Embraer Service Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
145-30-0044.......................... 01........................... June 26, 2006.
145-30-0044.......................... 02........................... September 25, 2006.
145-30-0044.......................... 03........................... December 12, 2006.
145-30-0044.......................... 04........................... May 14, 2008.
145-30-0049.......................... Original..................... June 28, 2006.
145-30-0049.......................... 01........................... October 19, 2006.
145LEG-30-0016....................... Original..................... June 28, 2006.
145LEG-30-0016....................... 01........................... February 5, 2007.
145LEG-30-0018....................... 02........................... December 12, 2006.
145LEG-30-0018....................... 03........................... May 14, 2008
----------------------------------------------------------------------------------------------------------------
Material Incorporated by Reference
(i) You must use the applicable service information contained in
Table 2 of this AD to do the actions required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical
Publications Section (PC 060), Av. Brigadeiro Faria Lima, 2170--
Putim--12227-901 S[atilde]o Jose dos Campos--SP--BRASIL; telephone:
+55 12 3927-5852 or +55 12 3309-0732; fax: +55 12 3927-7546; e-mail:
distrib@embraer.com.br; Internet: https://www.flyembraer.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Table 2--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Embraer Service Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
145LEG-30-0016....................... Original..................... June 28, 2006.
145LEG-30-0016....................... 01........................... February 5, 2007.
145LEG-30-0018....................... 02........................... December 12, 2006.
145LEG-30-0018....................... 03........................... May 14, 2008.
145-30-0044.......................... 01........................... June 26, 2006.
145-30-0044.......................... 02........................... September 25, 2006.
145-30-0044.......................... 03........................... December 12, 2006.
145-30-0044.......................... 04........................... May 14, 2008.
145-30-0049.......................... Original..................... June 28, 2006.
145-30-0049.......................... 01........................... October 19, 2006.
----------------------------------------------------------------------------------------------------------------
[[Page 66038]]
Issued in Renton, Washington, on December 1, 2009.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-29576 Filed 12-11-09; 8:45 am]
BILLING CODE 4910-13-P
