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, 60595-60598 [E7-21002]
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Federal Register / Vol. 72, No. 206 / Thursday, October 25, 2007 / Proposed Rules
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
EMPRESA BRASILEIRA DE
AERONAUTICA S.A. (EMBRAER):
Docket No. FAA–2007–27785;
Directorate Identifier 2006–NM–267–AD.
Comments Due Date
(a) We must receive comments by
November 19, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all EMBRAER Model
ERJ 170–100 LR, –100 STD, –100 SE, –100
SU, –200 LR, –200 STD, and –200 SU
airplanes, and Model ERJ 190–100 STD, –100
LR, –100 IGW, –200 STD, –200 LR, and –200
IGW airplanes; certificated in any category.
pwalker on PROD1PC71 with PROPOSALS
Subject
(d) Air Transport Association (ATA) of
America Code 22: Auto Flight.
17:49 Oct 24, 2007
Jkt 214001
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 300 flight hours after the
effective date of this AD, do a functional
check of the flight guidance control system
(FGCS) channels engagement, in accordance
with EMBRAER Service Bulletin 170–22–
0003 or EMBRAER Service Bulletin 190–22–
0002, both dated November 9, 2006, as
applicable. Repeat the functional check
thereafter at intervals not to exceed 600 flight
hours, until the optional terminating action
described by paragraph (f)(2) of this AD had
been done. If any malfunction of the FGCS
is discovered during any functional check
required by this paragraph, before further
flight, do all applicable replacements of the
actuator input-output processor in
accordance with the applicable service
bulletin.
Note 1: For the purpose of this AD, a
functional check is: ‘‘A quantitative check to
determine if one or more functions of an item
perform within specified limits.’’
(2) Installing PRIMUS EPIC Field-Loadable
Software Version 19.3, in accordance with
EMBRAER Service Bulletin 170–31–0019,
Revision 01, dated June 25, 2007; or Service
Bulletin 190–31–0009, Revision 02, dated
June 29, 2007, as applicable, ends the
repetitive functional checks required by
paragraph (f)(1) of this AD. If any software
versions higher than 19.3 are available, the
latest of any such versions is acceptable for
the installation described in this paragraph.
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, Attn: Todd Thompson,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Before using any approved AMOC on any
airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in
the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI Brazilian Airworthiness
Directives 2006–11–02 and 2006–11–03, both
effective November 16, 2006; EMBRAER
Service Bulletins 170–22–0003 and 190–22–
0002, both dated November 9, 2006;
EMBRAER Service Bulletin 170–31–0019,
Revision 01, dated June 25, 2007; and
EMBRAER Service Bulletin 190–31–0009,
Revision 02, dated June 29, 2007; for related
information.
Issued in Renton, Washington, on October
13, 2007.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–21008 Filed 10–24–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0083; Directorate
Identifier 2006–NM–266–AD]
RIN 2120–AA64
FAA AD Differences
Reason
(e) The mandatory continuing
airworthiness information (MCAI) for Model
ERJ 170 airplanes states:
It has been found that some ‘‘caution’’
messages issued by the Flight Guidance
Control System (FGCS) are not displayed on
aircraft equipped with EPIC software load
17.3 or 17.5. Therefore, following a possible
VerDate Aug<31>2005
failure on one FGCS channel during a given
flight, such a failure condition will remain
undetected or latent in subsequent flights. If
another failure occurs on the second FGCS
channel, the result may be a command
hardover by the autopilot.
The MCAI for Model ERJ 190 airplanes
states:
It has been found that some ‘‘caution’’
messages issued by the Flight Guidance
Control System (FGCS) are not displayed on
aircraft equipped with EPIC software load
4.3, 4.4 or 4.5. Therefore, following a possible
failure on one FGCS channel during a given
flight, such a failure condition will remain
undetected or latent in subsequent flights. If
another failure occurs on the second FGCS
channel, the result may be a command
hardover by the autopilot.
A command hardover is a sudden roll,
pitch, or yaw movement, which could result
in reduced controllability of the airplane.
The MCAI mandates a functional test of the
flight guidance control system channels
engagement. The corrective action is
replacement of the actuator input-output
processor if necessary.
60595
Note 2: This AD differs from the MCAI
and/or service information as follows: We
have provided optional terminating action in
paragraph (f)(2) of this AD; this difference
ˆ
has been coordinated with the Agencia
Nacional de Aviacao Civil (ANAC).
¸˜
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
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:
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Federal Aviation
Administration (FAA), DOT.
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60596
Federal Register / Vol. 72, No. 206 / Thursday, October 25, 2007 / Proposed Rules
Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
SUMMARY:
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.
pwalker on PROD1PC71 with PROPOSALS
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by November 26,
2007.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1175;
fax (425) 227–1149.
VerDate Aug<31>2005
17:49 Oct 24, 2007
Jkt 214001
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–0083; Directorate Identifier
2006–NM–266–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
ˆ
The Agencia Nacional de Aviacao
¸˜
Civil (ANAC), which is the aviation
authority for Brazil, has issued Brazilian
Airworthiness Directive 2006–09–03R1,
effective January 4, 2007 (referred to
after this as ‘‘the MCAI’’), 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), since the engine anti-ice system valve
be 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 MCAI requires inspection of the
engine anti-icing system valves and
tubes to detect damage and, if necessary,
replacement of the anti-icing system
valves. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
EMBRAER has issued the following
service bulletins:
• 145–30–0044, Revision 03, dated
December 12, 2006.
• 145–30–0049, Revision 01, dated
October 19, 2006.
• 145LEG–30–0016, Revision 01,
dated February 5, 2007.
• 145LEG–30–0018, Revision 02,
dated December 12, 2006.
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Fmt 4702
Sfmt 4702
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a NOTE within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 697 products of U.S.
registry. We also estimate that it would
take about 2 work-hours per product to
comply with the requirements of this
proposed AD. The average labor rate is
$80 per work-hour. Based on these
figures, we estimate the cost of the
proposed AD on U.S. operators to be
$111,520, or $160 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
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Federal Register / Vol. 72, No. 206 / Thursday, October 25, 2007 / 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.
Applicability
(c) This AD applies to Empresa Brasileira
de Aeronautica S.A. (EMBRAER) Model
EMB–135BJ, –135ER, –135KE, –135KL,
–135LR, –145, –145ER, –145MR, –145LR,
–145XR, –145MP, and –145EP airplanes,
certificated in any category, except aircraft
having serial numbers 14500921, 14500928,
14500932, 14500949, 14500958, 14500971,
14500973 and up, which will have in-factory
modification incorporated.
Regulatory Findings
Subject
(d) Air Transport Association of America
Code 30: Ice and Rain Protection.
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
pwalker on PROD1PC71 with PROPOSALS
2. The FAA amends § 39.13 by adding
the following new AD:
EMPRESA BRASILEIRA DE
AERONAUTICA S.A. (EMBRAER):
Docket No. FAA–2007–0083; Directorate
Identifier 2006–NM–266–AD.
Comments Due Date
(a) We must receive comments by
November 26, 2007.
Affected ADs
(b) None.
VerDate Aug<31>2005
17:49 Oct 24, 2007
Jkt 214001
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), since the engine anti-ice system valve
be 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 MCAI requires inspection of the
engine anti-icing system valves and tubes to
detect damage and, if necessary, replacement
of the anti-icing system valves.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) PART I—Within the next 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 (lefthand) and RH (right-hand) engine anti-ice
system valves to determine their P/N (part
number).
(i) If any engine anti-ice system valve with
P/N C146009–2 is found, no further action is
required by paragraph (f)(1) of this AD.
(ii) If any anti-ice system valve with P/N
C146009–3 is found, before further flight:
Remove it 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, Revision 01, dated
October 19, 2006; or 145LEG–30–0016,
Revision 01, dated February 5, 2007; as
applicable.
(A) If the valve is damaged or the tube is
obstructed, as shown in EMBRAER Service
Bulletin 145–30–0049, Revision 01, dated
October 19, 2006; or 145LEG–30–0016,
Revision 01, dated February 5, 2007; as
applicable; before further flight: Replace the
valve with another one bearing P/N
C146009–2, C146009–3, or C146009–4; or
remove the obstruction; as applicable; in
accordance with the Accomplishment
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60597
Instructions of the applicable service
bulletin.
(B) If the valve is not damaged or the tube
is not obstructed, re-install the valve or
install another one bearing P/N C146009–2,
C146009–3, or C146009–4; or re-install the
tube; in accordance with the
Accomplishment Instructions of the
applicable service bulletin.
(iii) If any engine anti-ice system valve
with P/N C146009–4 is found, 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 the next 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 antiice 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, Revision 01, dated October 19,
2006; or 145LEG–30–0016, Revision 01,
dated February 5, 2007; as applicable;
accomplishing paragraphs (f)(2)(i) and
(f)(2)(ii) of this AD.
(i) If the valve is damaged or the tube is
obstructed, as shown in EMBRAER Service
Bulletin 145–30–0049, Revision 01, dated
October 19, 2006; or 145LEG–30–0016,
Revision 01, dated February 5, 2007; as
applicable; before further flight: Replace the
valve with another one bearing P/N
C146009–2, C146009–3, or C146009–4; or
remove the obstruction; as applicable; in
accordance with the Accomplishment
Instructions of the applicable service
bulletin.
(ii) If the valve is not damaged, and the
tube is not obstructed, before further flight:
Re-install the valve or install another one
bearing P/N C146009–2, C146009–3, or
C146009–4; or remove the obstruction; as
applicable; in accordance with the
Accomplishment Instructions of EMBRAER
Service Bulletin 145–30–0049, Revision 01,
dated October 19, 2006; or 145LEG–30–0016,
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 paragraph (f)(1) and (f)(2) of
this AD, must undergo a detailed inspection
for its integrity before installation, and any
damage or obstruction repaired, according to
the detailed instructions and procedures
described in EMBRAER Service Bulletin
145–30–0049, Revision 01, dated October 19,
2006; or 145LEG–30–0016, Revision 01,
dated February 5, 2007; as applicable; and
additionally adhere to paragraphs (f)(3)(i) and
(f)(3)(ii) of this AD.
(i) If the valve is damaged, replace it by
another one bearing P/N C146009–2,
C146009–3, or C146009–4; in accordance
with the Accomplishment Instructions of the
applicable service bulletin.
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60598
Federal Register / Vol. 72, No. 206 / Thursday, October 25, 2007 / Proposed Rules
(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 aircraft as
a replacement as provided for in paragraph
(f)(1) and (f)(2) of this AD, must undergo a
special detailed inspection before
installation, and any damage or obstruction
repaired, according to the detailed
instructions and procedures described in
EMBRAER Service Bulletin 145–30–0049,
Revision 01, dated October 19, 2006; or
145LEG–30–0016, 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 the
next 1,500 flight hours or 9 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,
or Revision 03, dated December 12, 2006; or
145LEG–30–0018, Revision 02, dated
December 12, 2006; as applicable; no further
action is required by this AD.
(ii) If the valve was installed according to
the detailed instructions and procedures
described in EMBRAER Service Bulletin
145–30–0044, Revision 03, dated December
12, 2006; 145LEG–30–0018, dated June 26,
2006; or 145LEG–30–0018, Revision 01,
dated September 25, 2006; as applicable;
carry out a special detailed inspection in the
corresponding engine anti-ice system tubes,
and repair any damage or remove any
obstruction; according to the detailed
instructions and procedures described in
EMBRAER Service Bulletin 145–30–0049,
Revision 01, dated October 19, 2006; or
145LEG–30–0016, Revision 01, dated
February 5, 2007; as applicable.
(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 repair any damage or obstruction before
further flight. Do all actions according to the
detailed instructions and procedures
described in EMBRAER Service Bulletin
145–30–0049, Revision 01, dated October 19,
2006; or 145LEG–30–0016, Revision 01,
dated February 5, 2007; as applicable;
accomplishing paragraph (f)(2) of this AD,
unless:
(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,
Revision 03, dated December 12, 2006; or
145LEG–30–0018, dated June 26, 2006; or
145LEG–30–0018, Revision 01, dated
September 25, 2006; as applicable; and
additionally, paragraph (f)(5)(ii) of this AD
has been accomplished; or
(ii) Valves with P/N C146009–4 have been
previously installed according to the detailed
VerDate Aug<31>2005
17:49 Oct 24, 2007
Jkt 214001
instructions and procedures described in
EMBRAER Service Bulletin 145–30–0044,
Revision 01, dated June 26, 2006, or Revision
02, dated September 25, 2006; or 145LEG–
30–0018, Revision 02, dated December 12,
2006; as applicable.
(7) PART VII—Within the next 2,500 flight
hours or 12 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, or Revision 03, dated December 12,
2006; or 145LEG–30–0018, Revision 02,
dated December 12, 2006; as applicable.
(8) PART VIII—Within the next 6,000 flight
hours or 30 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, or Revision 03, dated December 12,
2006; or 145LEG–30–0018, Revision 02,
dated December 12, 2006; as applicable.
(9) 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, or Revision 03, dated December 12,
2006; or 145LEG–30–0018, Revision 02,
dated December 12, 2006; as applicable;
constitutes a terminating action for this AD,
in lieu of the repetitive inspections required
by paragraph (f)(2) of 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.’’
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: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, 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: Todd Thompson,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1175; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI Brazilian Airworthiness
Directive 2006–09–03R1, effective January 4,
2007; and EMBRAER Service Bulletins 145–
30–0044, Revision 03, dated December 12,
2006; 145–30–0049, Revision 01, dated
October 19, 2006; 145LEG–30–0016, Revision
01, dated February 5, 2007; and 145LEG–30–
0018, Revision 02, dated December 12, 2006;
for related information.
Issued in Renton, Washington, on October
15, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–21002 Filed 10–24–07; 8:45 am]
BILLING CODE 4910–13–P
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
PO 00000
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]]>Agencies
[Federal Register Volume 72, Number 206 (Thursday, October 25, 2007)]
[Proposed Rules]
[Pages 60595-60598]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-21002]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0083; Directorate Identifier 2006-NM-266-AD]
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), DOT.
[[Page 60596]]
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
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.
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by November 26,
2007.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0083;
Directorate Identifier 2006-NM-266-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC),
which is the aviation authority for Brazil, has issued Brazilian
Airworthiness Directive 2006-09-03R1, effective January 4, 2007
(referred to after this as ``the MCAI''), 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), since
the engine anti-ice system valve be 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 MCAI requires inspection of the engine anti-icing system valves
and tubes to detect damage and, if necessary, replacement of the anti-
icing system valves. You may obtain further information by examining
the MCAI in the AD docket.
Relevant Service Information
EMBRAER has issued the following service bulletins:
145-30-0044, Revision 03, dated December 12, 2006.
145-30-0049, Revision 01, dated October 19, 2006.
145LEG-30-0016, Revision 01, dated February 5, 2007.
145LEG-30-0018, Revision 02, dated December 12, 2006.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 697 products of U.S. registry. We also estimate that
it would take about 2 work-hours per product to comply with the
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $111,520, or $160 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
[[Page 60597]]
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
EMPRESA BRASILEIRA DE AERONAUTICA S.A. (EMBRAER): Docket No. FAA-
2007-0083; Directorate Identifier 2006-NM-266-AD.
Comments Due Date
(a) We must receive comments by November 26, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Empresa Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, -145, -
145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes,
certificated in any category, except aircraft 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), since
the engine anti-ice system valve be 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 MCAI requires inspection of the engine anti-icing system
valves and tubes to detect damage and, if necessary, replacement of
the anti-icing system valves.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) PART I--Within the next 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) If any engine anti-ice system valve with P/N C146009-2 is
found, no further action is required by paragraph (f)(1) of this AD.
(ii) If any anti-ice system valve with P/N C146009-3 is found,
before further flight: Remove it 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, Revision 01,
dated October 19, 2006; or 145LEG-30-0016, Revision 01, dated
February 5, 2007; as applicable.
(A) If the valve is damaged or the tube is obstructed, as shown
in EMBRAER Service Bulletin 145-30-0049, Revision 01, dated October
19, 2006; or 145LEG-30-0016, Revision 01, dated February 5, 2007; as
applicable; before further flight: Replace the valve with another
one bearing P/N C146009-2, C146009-3, or C146009-4; or remove the
obstruction; as applicable; in accordance with the Accomplishment
Instructions of the applicable service bulletin.
(B) If the valve is not damaged or the tube is not obstructed,
re-install the valve or install another one bearing P/N C146009-2,
C146009-3, or C146009-4; or re-install the tube; in accordance with
the Accomplishment Instructions of the applicable service bulletin.
(iii) If any engine anti-ice system valve with P/N C146009-4 is
found, 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 the next 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, Revision 01, dated October 19,
2006; or 145LEG-30-0016, Revision 01, dated February 5, 2007; as
applicable; accomplishing paragraphs (f)(2)(i) and (f)(2)(ii) of
this AD.
(i) If the valve is damaged or the tube is obstructed, as shown
in EMBRAER Service Bulletin 145-30-0049, Revision 01, dated October
19, 2006; or 145LEG-30-0016, Revision 01, dated February 5, 2007; as
applicable; before further flight: Replace the valve with another
one bearing P/N C146009-2, C146009-3, or C146009-4; or remove the
obstruction; as applicable; in accordance with the Accomplishment
Instructions of the applicable service bulletin.
(ii) If the valve is not damaged, and the tube is not
obstructed, before further flight: Re-install the valve or install
another one bearing P/N C146009-2, C146009-3, or C146009-4; or
remove the obstruction; as applicable; in accordance with the
Accomplishment Instructions of EMBRAER Service Bulletin 145-30-0049,
Revision 01, dated October 19, 2006; or 145LEG-30-0016, 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 paragraph (f)(1) and (f)(2) of this AD, must undergo a
detailed inspection for its integrity before installation, and any
damage or obstruction repaired, according to the detailed
instructions and procedures described in EMBRAER Service Bulletin
145-30-0049, Revision 01, dated October 19, 2006; or 145LEG-30-0016,
Revision 01, dated February 5, 2007; as applicable; and additionally
adhere to paragraphs (f)(3)(i) and (f)(3)(ii) of this AD.
(i) If the valve is damaged, replace it by another one bearing
P/N C146009-2, C146009-3, or C146009-4; in accordance with the
Accomplishment Instructions of the applicable service bulletin.
[[Page 60598]]
(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 aircraft as a replacement as provided for in
paragraph (f)(1) and (f)(2) of this AD, must undergo a special
detailed inspection before installation, and any damage or
obstruction repaired, according to the detailed instructions and
procedures described in EMBRAER Service Bulletin 145-30-0049,
Revision 01, dated October 19, 2006; or 145LEG-30-0016, 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 the next 1,500 flight hours or 9 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, or Revision 03, dated December 12, 2006; or
145LEG-30-0018, Revision 02, dated December 12, 2006; as applicable;
no further action is required by this AD.
(ii) If the valve was installed according to the detailed
instructions and procedures described in EMBRAER Service Bulletin
145-30-0044, Revision 03, dated December 12, 2006; 145LEG-30-0018,
dated June 26, 2006; or 145LEG-30-0018, Revision 01, dated September
25, 2006; as applicable; carry out a special detailed inspection in
the corresponding engine anti-ice system tubes, and repair any
damage or remove any obstruction; according to the detailed
instructions and procedures described in EMBRAER Service Bulletin
145-30-0049, Revision 01, dated October 19, 2006; or 145LEG-30-0016,
Revision 01, dated February 5, 2007; as applicable.
(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 repair any damage or obstruction before further
flight. Do all actions according to the detailed instructions and
procedures described in EMBRAER Service Bulletin 145-30-0049,
Revision 01, dated October 19, 2006; or 145LEG-30-0016, Revision 01,
dated February 5, 2007; as applicable; accomplishing paragraph
(f)(2) of this AD, unless:
(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, Revision 03, dated December
12, 2006; or 145LEG-30-0018, dated June 26, 2006; or 145LEG-30-0018,
Revision 01, dated September 25, 2006; as applicable; and
additionally, paragraph (f)(5)(ii) of this AD has been accomplished;
or
(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, or Revision 02, dated September 25, 2006; or 145LEG-30-0018,
Revision 02, dated December 12, 2006; as applicable.
(7) PART VII--Within the next 2,500 flight hours or 12 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, or Revision 03, dated December 12, 2006; or
145LEG-30-0018, Revision 02, dated December 12, 2006; as applicable.
(8) PART VIII--Within the next 6,000 flight hours or 30 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, or Revision 03, dated December 12, 2006; or
145LEG-30-0018, Revision 02, dated December 12, 2006; as applicable.
(9) 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, or
Revision 03, dated December 12, 2006; or 145LEG-30-0018, Revision
02, dated December 12, 2006; as applicable; constitutes a
terminating action for this AD, in lieu of the repetitive
inspections required by paragraph (f)(2) of 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: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, 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: Todd
Thompson, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to MCAI Brazilian Airworthiness Directive 2006-09-
03R1, effective January 4, 2007; and EMBRAER Service Bulletins 145-
30-0044, Revision 03, dated December 12, 2006; 145-30-0049, Revision
01, dated October 19, 2006; 145LEG-30-0016, Revision 01, dated
February 5, 2007; and 145LEG-30-0018, Revision 02, dated December
12, 2006; for related information.
Issued in Renton, Washington, on October 15, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-21002 Filed 10-24-07; 8:45 am]
BILLING CODE 4910-13-P
