Airworthiness Directives; Fokker Model F.28 Mark 0070 and Mark 0100 Airplanes, 21233-21235 [E8-8256]
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21233
Federal Register / Vol. 73, No. 77 / Monday, April 21, 2008 / Rules and Regulations
AFM, and the copy of this AD may be
removed from the AFM.
New Requirements of This AD
AFM Revision for New Airplanes
(g) For Model ERJ 170–200 LR, –200 STD,
and –200 SU airplanes; and Model ERJ 190–
200 IGW, –200 LR, and –200 STD airplanes:
Within 14 days after the effective date of this
AD, revise the Limitations section of the
EMBRAER 170/190 AFM to include the
following statement. This may be done by
inserting a copy of this AD in the AFM.
Factory-installation or installation of the
applicable software required by paragraph (h)
of this AD terminates the AFM revision
required by this paragraph.
‘‘After applying thrust reverser, do not
move the throttle back to the forward thrust
range, unless the REV icon on the EICAS is
shown in amber or green.’’
Note 2: When a statement identical to that
in paragraph (g) of this AD has been included
in the general revisions of the AFM, the
general revisions may be inserted into the
AFM, and the copy of this AD may be
removed from the AFM.
Software Installation
(h) Within 1,200 flight hours after the
effective date of this AD, install the fullauthority digital engine-control (FADEC)
software specified in paragraph (h)(1), (h)(2),
or (h)(3) of this AD, as applicable. Installing
the applicable software terminates the
applicable AFM revision required by
paragraph (f) or (g) of this AD.
(1) For Model ERJ 170–100 LR, –100 SE,
–100 STD, –100 SU, –200 LR, –200 STD, and
–200 SU airplanes identified in EMBRAER
Service Bulletin 170–73–0003, Revision 01,
dated September 4, 2006: Install engine
FADEC software version 5.30 or higher in
accordance with the service bulletin.
(2) For the Model ERJ 190–200 LR airplane
identified in EMBRAER Service Bulletin
190–73–0005, dated November 9, 2006:
Install engine FADEC software version 5.10
or higher in accordance with the service
bulletin.
(3) For Model ERJ 190–100 IGW, –100 LR,
–100 STD, –200 IGW, –200 LR, and –200 STD
airplanes identified in EMBRAER Service
Bulletin 190–73–0009, Revision 01, dated
April 23, 2007: Install engine FADEC
software version 5.20 or higher in accordance
with the service bulletin.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(j) Brazilian airworthiness directive 2006–
03–02R1, effective February 27, 2007; and
Brazilian airworthiness directive 2006–03–
03R1, effective November 9, 2007; also
address the subject of this AD.
Material Incorporated by Reference
(k) You must use the service information
listed in Table 1 of this AD to perform the
actions that are required by this AD, as
applicable, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of these documents in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Empresa Brasileira de Aeronautica
S.A. (EMBRAER), P.O. Box 343–CEP 12.225,
Sao Jose dos Campos–SP, Brazil, for a copy
of this service information. You may review
copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or 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/
cfr/ibr-locations.html.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
EMBRAER Service Bulletin
Revision level
170–73–0003 ........................................................................
190–73–0005 ........................................................................
190–73–0009 ........................................................................
01 .........................................................................................
Original .................................................................................
01 .........................................................................................
Issued in Renton, Washington, on April 8,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–8255 Filed 4–18–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0117; Directorate
Identifier 2007–NM–273–AD; Amendment
39–15472; AD 2008–08–18]
rfrederick on PROD1PC67 with RULES
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.28 Mark 0070 and Mark 0100
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
VerDate Aug<31>2005
15:19 Apr 18, 2008
Jkt 214001
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:
[L]eakage of hot wing anti-icing air from
the Peri-seal housing. This results in an
uncontrolled flow of high-pressure hot air to
enter the forward (anti-icing) plenum
chamber of the wing leading edge, potentially
damaging the anti-icing barrier webs.
Subsequently, the wing auxiliary spar can
also be damaged by high-pressure hot air.
* * * [D]eterioration of the Peri-seals
enables the piccolo tubes to vibrate, resulting
in a broken piccolo tube. * * * This
condition, if not corrected, may cause heat
damage to the front spar that potentially
affects the wing’s load capability.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
Date
September 4, 2006.
November 9, 2006.
April 23, 2007.
This AD becomes effective May
27, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 27, 2008.
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: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
DATES:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
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21APR1
21234
Federal Register / Vol. 73, No. 77 / Monday, April 21, 2008 / Rules and Regulations
apply to the specified products. That
NPRM was published in the Federal
Register on February 5, 2008 (73 FR
6629). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
In 1997, Fokker introduced a new type of
Peri-seal (SBF100–30–022). The old type was
known to be subject to deterioration, which,
in combination with improper installation,
can cause leakage of hot wing anti-icing air
from the Peri-seal housing. This results in an
uncontrolled flow of high-pressure hot air to
enter the forward (anti-icing) plenum
chamber of the wing leading edge, potentially
damaging the anti-icing barrier webs.
Subsequently, the wing auxiliary spar can
also be damaged by high-pressure hot air.
Analysis at the time showed that any
resulting damage (known to occur at inboard
positions only) would not affect the wing
load capability. For this reason, the
modification was not classified as
MANDATORY and no AD action was
warranted. However, through a recent
occurrence, it was discovered that
deterioration of the Peri-seals enables the
piccolo tubes to vibrate, resulting in a broken
piccolo tube. In this case, the location of the
failure was more outboard than previous
occurrences. This condition, if not corrected,
may cause heat damage to the front spar that
potentially affects the wing’s load capability.
Since an unsafe condition was identified,
likely to exist or develop on an aircraft of this
type design, CAA (Civil Aviation Authority)
Netherlands issued AD NL–2006–011 to
require inspection of the Piccolo Tubes and
the surrounding structure to establish correct
installation, as well as the replacement of the
460-series Peri-seals by the improved 600series, which have a higher temperature
limit.
Since the issuance of that AD, Fokker has
developed a modification, published as
Component Service Bulletin (CSB) D14000–
57–007, for spare wing leading edge sections
that may still contain the 460-series Periseals. For that reason, this EASA AD retains
the requirements of AD NL–2006–011 and
adds a limit for the allowed use of
unmodified wing leading edge section as
replacement part.
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
about 9 products of U.S. registry. We
also estimate that it will take about 48
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts will cost about $3,430
per product. Where the service
information lists required parts costs
that are covered under warranty, we
have assumed that there will be no
charge for these parts. 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
this AD to the U.S. operators to be
$65,430, or $7,270 per product.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
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.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
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
rfrederick on PROD1PC67 with RULES
The corrective actions include
inspection of the piccolo tubes and the
wing leading edge for damage, and
replacement of the Peri-seals, or repair
of damage, as applicable. You may
obtain further information by examining
the MCAI in the AD docket.
VerDate Aug<31>2005
15:19 Apr 18, 2008
Jkt 214001
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2008–08–18 Fokker Services B.V.:
Amendment 39–15472. Docket No.
FAA–2008–0117; Directorate Identifier
2007–NM–273–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective May 27, 2008.
Affected ADs
(b) None.
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Federal Register / Vol. 73, No. 77 / Monday, April 21, 2008 / Rules and Regulations
Applicability
(c) This AD applies to Fokker Model F.28
Mark 0070 and Mark 0100 airplanes,
certificated in any category, all serial
numbers, except those previously modified
in accordance with Fokker Service Bulletin
SBF100–30–022.
Subject
(d) Air Transport Association (ATA) of
America Code 30: Ice and Rain Protection.
Reason
rfrederick on PROD1PC67 with RULES
(e) The mandatory continuing
airworthiness information (MCAI) states:
In 1997, Fokker introduced a new type of
Peri-seal (SBF100–30–022). The old type was
known to be subject to deterioration, which,
in combination with improper installation,
can cause leakage of hot wing anti-icing air
from the Peri-seal housing. This results in an
uncontrolled flow of high-pressure hot air to
enter the forward (anti-icing) plenum
chamber of the wing leading edge, potentially
damaging the anti-icing barrier webs.
Subsequently, the wing auxiliary spar can
also be damaged by high-pressure hot air.
Analysis at the time showed that any
resulting damage (known to occur at inboard
positions only) would not affect the wing
load capability. For this reason, the
modification was not classified as
MANDATORY and no AD action was
warranted. However, through a recent
occurrence, it was discovered that
deterioration of the Peri-seals enables the
piccolo tubes to vibrate, resulting in a broken
piccolo tube. In this case, the location of the
failure was more outboard than previous
occurrences. This condition, if not corrected,
may cause heat damage to the front spar that
potentially affects the wing’s load capability.
Since an unsafe condition was identified,
likely to exist or develop on an aircraft of this
type design, CAA (Civil Aviation Authority)
Netherlands issued AD NL–2006–011 to
require inspection of the Piccolo Tubes and
the surrounding structure to establish correct
installation, as well as the replacement of the
460-series Peri-seals by the improved 600series, which have a higher temperature
limit.
Since the issuance of that AD, Fokker has
developed a modification, published as
Component Service Bulletin (CSB) D14000–
57–007, for spare wing leading edge sections
that may still contain the 460-series Periseals. For that reason, this EASA AD retains
the requirements of AD NL–2006–011 and
adds a limit for the allowed use of
unmodified wing leading edge section as
replacement part.
The corrective actions include inspection
of the piccolo tubes and the wing leading
edge for damage, and replacement of the Periseals, or repair of damage, as applicable.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 4,000 flight hours or 12 months
after the effective date of this AD, whichever
occurs first, do the actions in paragraphs
(f)(1)(i) and (f)(1)(ii) of this AD in accordance
with the Accomplishment Instructions of
VerDate Aug<31>2005
15:19 Apr 18, 2008
Jkt 214001
Fokker Service Bulletin SBF100–30–028,
Revision 1, dated April 17, 2007.
(i) Inspect for damage of the piccolo tubes
and the wing leading edge on the outside and
on the inside at the access panels. If any
damage is found that is beyond the limits
specified in the service bulletin, repair before
further flight.
(ii) Replace the 460-series Peri-seals in the
riblets with improved 600-series Peri-seals.
(2) As of 12 months after the effective date
of this AD, no person may install on any
airplane a spare wing leading edge section
unless the leading edge section has been
modified in accordance with Fokker
Component Service Bulletin D14000–57–007,
dated April 17, 2007.
(3) Actions done before the effective date
of this AD in accordance with Fokker Service
Bulletin SBF100–30–028, dated May 18,
2006, are considered acceptable for
compliance with the actions required by
paragraph (f)(1) of this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
Related Information
(h) Refer to European Aviation Safety
Agency (EASA) Airworthiness Directive
2007–0229, dated August 15, 2007; Fokker
Service Bulletin SBF100–30–028, Revision 1,
dated April 17, 2007; and Fokker Component
Service Bulletin D14000–57–007, dated April
17, 2007; for related information.
Frm 00021
Fmt 4700
Sfmt 4700
Material Incorporated by Reference
(i) You must use Fokker Service Bulletin
SBF100–30–028, Revision 1, dated April 17,
2007, 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 Fokker Services B.V.,
Technical Services Dept., P.O. Box 231, 2150
AE Nieuw-Vennep, the Netherlands.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on April 8,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–8256 Filed 4–18–08; 8:45 am]
BILLING CODE 4910–13–P
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tom Rodriguez,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1137; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved 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.
PO 00000
21235
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29063; Directorate
Identifier 2007–NM–049–AD; Amendment
39–15480; AD 2008–08–26]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
Boeing Model 767 airplanes. This AD
requires a one-time inspection to
determine the material of the forward
and aft gray water drain masts. For
airplanes having composite gray water
drain masts, this AD also requires
installation of a ground bracket and a
bonding jumper between a ground
bracket and the clamp on the tube of the
forward and aft gray water composite
drain masts. This AD results from a
report of charred insulation blankets
and burned wires around the forward
gray water composite drain mast found
during an inspection of the forward
cargo compartment. We are issuing this
AD to prevent a fire near a composite
drain mast and possible disruption of
the electrical power system caused by a
lightning strike on a composite drain
E:\FR\FM\21APR1.SGM
21APR1
]]>Agencies
[Federal Register Volume 73, Number 77 (Monday, April 21, 2008)]
[Rules and Regulations]
[Pages 21233-21235]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-8256]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0117; Directorate Identifier 2007-NM-273-AD;
Amendment 39-15472; AD 2008-08-18]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.28 Mark 0070 and Mark
0100 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:
[L]eakage of hot wing anti-icing air from the Peri-seal housing.
This results in an uncontrolled flow of high-pressure hot air to
enter the forward (anti-icing) plenum chamber of the wing leading
edge, potentially damaging the anti-icing barrier webs.
Subsequently, the wing auxiliary spar can also be damaged by high-
pressure hot air. * * * [D]eterioration of the Peri-seals enables
the piccolo tubes to vibrate, resulting in a broken piccolo tube. *
* * This condition, if not corrected, may cause heat damage to the
front spar that potentially affects the wing's load capability.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective May 27, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 27, 2008.
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: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
[[Page 21234]]
apply to the specified products. That NPRM was published in the Federal
Register on February 5, 2008 (73 FR 6629). That NPRM proposed to
correct an unsafe condition for the specified products. The MCAI
states:
In 1997, Fokker introduced a new type of Peri-seal (SBF100-30-
022). The old type was known to be subject to deterioration, which,
in combination with improper installation, can cause leakage of hot
wing anti-icing air from the Peri-seal housing. This results in an
uncontrolled flow of high-pressure hot air to enter the forward
(anti-icing) plenum chamber of the wing leading edge, potentially
damaging the anti-icing barrier webs. Subsequently, the wing
auxiliary spar can also be damaged by high-pressure hot air.
Analysis at the time showed that any resulting damage (known to
occur at inboard positions only) would not affect the wing load
capability. For this reason, the modification was not classified as
MANDATORY and no AD action was warranted. However, through a recent
occurrence, it was discovered that deterioration of the Peri-seals
enables the piccolo tubes to vibrate, resulting in a broken piccolo
tube. In this case, the location of the failure was more outboard
than previous occurrences. This condition, if not corrected, may
cause heat damage to the front spar that potentially affects the
wing's load capability. Since an unsafe condition was identified,
likely to exist or develop on an aircraft of this type design, CAA
(Civil Aviation Authority) Netherlands issued AD NL-2006-011 to
require inspection of the Piccolo Tubes and the surrounding
structure to establish correct installation, as well as the
replacement of the 460-series Peri-seals by the improved 600-series,
which have a higher temperature limit.
Since the issuance of that AD, Fokker has developed a
modification, published as Component Service Bulletin (CSB) D14000-
57-007, for spare wing leading edge sections that may still contain
the 460-series Peri-seals. For that reason, this EASA AD retains the
requirements of AD NL-2006-011 and adds a limit for the allowed use
of unmodified wing leading edge section as replacement part.
The corrective actions include inspection of the piccolo tubes and
the wing leading edge for damage, and replacement of the Peri-seals, or
repair of damage, as applicable. 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 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 about 9 products of U.S.
registry. We also estimate that it will take about 48 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $80 per work-hour. Required parts will cost about $3,430
per product. Where the service information lists required parts costs
that are covered under warranty, we have assumed that there will be no
charge for these parts. 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 this AD to the
U.S. operators to be $65,430, or $7,270 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this 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:
2008-08-18 Fokker Services B.V.: Amendment 39-15472. Docket No. FAA-
2008-0117; Directorate Identifier 2007-NM-273-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 27,
2008.
Affected ADs
(b) None.
[[Page 21235]]
Applicability
(c) This AD applies to Fokker Model F.28 Mark 0070 and Mark 0100
airplanes, certificated in any category, all serial numbers, except
those previously modified in accordance with Fokker Service Bulletin
SBF100-30-022.
Subject
(d) Air Transport Association (ATA) of America Code 30: Ice and
Rain Protection.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
In 1997, Fokker introduced a new type of Peri-seal (SBF100-30-
022). The old type was known to be subject to deterioration, which,
in combination with improper installation, can cause leakage of hot
wing anti-icing air from the Peri-seal housing. This results in an
uncontrolled flow of high-pressure hot air to enter the forward
(anti-icing) plenum chamber of the wing leading edge, potentially
damaging the anti-icing barrier webs. Subsequently, the wing
auxiliary spar can also be damaged by high-pressure hot air.
Analysis at the time showed that any resulting damage (known to
occur at inboard positions only) would not affect the wing load
capability. For this reason, the modification was not classified as
MANDATORY and no AD action was warranted. However, through a recent
occurrence, it was discovered that deterioration of the Peri-seals
enables the piccolo tubes to vibrate, resulting in a broken piccolo
tube. In this case, the location of the failure was more outboard
than previous occurrences. This condition, if not corrected, may
cause heat damage to the front spar that potentially affects the
wing's load capability. Since an unsafe condition was identified,
likely to exist or develop on an aircraft of this type design, CAA
(Civil Aviation Authority) Netherlands issued AD NL-2006-011 to
require inspection of the Piccolo Tubes and the surrounding
structure to establish correct installation, as well as the
replacement of the 460-series Peri-seals by the improved 600-series,
which have a higher temperature limit.
Since the issuance of that AD, Fokker has developed a
modification, published as Component Service Bulletin (CSB) D14000-
57-007, for spare wing leading edge sections that may still contain
the 460-series Peri-seals. For that reason, this EASA AD retains the
requirements of AD NL-2006-011 and adds a limit for the allowed use
of unmodified wing leading edge section as replacement part.
The corrective actions include inspection of the piccolo tubes
and the wing leading edge for damage, and replacement of the Peri-
seals, or repair of damage, as applicable.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 4,000 flight hours or 12 months after the effective
date of this AD, whichever occurs first, do the actions in
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD in accordance with
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
30-028, Revision 1, dated April 17, 2007.
(i) Inspect for damage of the piccolo tubes and the wing leading
edge on the outside and on the inside at the access panels. If any
damage is found that is beyond the limits specified in the service
bulletin, repair before further flight.
(ii) Replace the 460-series Peri-seals in the riblets with
improved 600-series Peri-seals.
(2) As of 12 months after the effective date of this AD, no
person may install on any airplane a spare wing leading edge section
unless the leading edge section has been modified in accordance with
Fokker Component Service Bulletin D14000-57-007, dated April 17,
2007.
(3) Actions done before the effective date of this AD in
accordance with Fokker Service Bulletin SBF100-30-028, dated May 18,
2006, are considered acceptable for compliance with the actions
required by paragraph (f)(1) of this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN: Tom
Rodriguez, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to European Aviation Safety Agency (EASA)
Airworthiness Directive 2007-0229, dated August 15, 2007; Fokker
Service Bulletin SBF100-30-028, Revision 1, dated April 17, 2007;
and Fokker Component Service Bulletin D14000-57-007, dated April 17,
2007; for related information.
Material Incorporated by Reference
(i) You must use Fokker Service Bulletin SBF100-30-028, Revision
1, dated April 17, 2007, 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
Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150
AE Nieuw-Vennep, the Netherlands.
(3) You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/cfr/ibr-
locations.html.
Issued in Renton, Washington, on April 8, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-8256 Filed 4-18-08; 8:45 am]
BILLING CODE 4910-13-P
