Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 17694-17696 [06-3196]
Download as PDF
<![CDATA[
17694
Federal Register / Vol. 71, No. 67 / Friday, April 7, 2006 / Rules and Regulations
Terminating Action
(j) At the applicable compliance time in
paragraph (j)(1) or (j)(2) of this AD, replace
any MLG bogie beam pivot pin having P/N
161T1145–2, –3, or –4, with a new, improved
pivot pin having P/N 161T1145–5; and do all
applicable related investigative and
corrective actions before further flight; in
accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–32A0199, Revision 2,
dated May 26, 2005. Where the Note at the
end of Table 1 in paragraph 1.E.,
‘‘Compliance,’’ of the service bulletin
specifies to contact Boeing for a longer
compliance time for ‘‘Group 2 airplanes that
have been operated at weights less than
353,000 pounds since pivot pin installation’’:
Operators must contact the Manager, Seattle
ACO, for an alternative method of
compliance in accordance with paragraph (l)
of this AD for any requests for a longer
compliance time. Doing the replacement in
accordance with this paragraph terminates
the requirements of this AD for that pivot
pin.
(1) For airplanes identified in the service
bulletin as Group 1 airplanes: Within 96
months after the effective date of this AD.
(2) For airplanes identified in the service
bulletin as Group 2 airplanes: Within 48
months after the effective date of this AD.
Actions Accomplished According to
Previous Issues of Service Bulletin
(k) Replacing any pivot pin with a new,
improved pivot pin having P/N 161T1145–5,
before the effective date of this AD in
accordance with the service bulletins
identified in Table 1 of this AD is considered
acceptable for compliance with the
corresponding action specified in this AD.
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Boeing Alert
Service Bulletin
Revision
767–32A0199
767–32A0199
wwhite on PROD1PC65 with RULES
Issued in Renton, Washington, on March
24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–3194 Filed 4–6–06; 8:45 am]
[Docket No. FAA–2006–23798; Directorate
Identifier 2005–NM–162–AD; Amendment
39–14543; AD 2006–07–16]
TABLE 1.—PREVIOUS ISSUES OF
SERVICE BULLETIN
Original ....
1 ..............
Date
April 8, 2004.
July 22, 2004.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
VerDate Aug<31>2005
Material Incorporated by Reference
(m) You must use Boeing Alert Service
Bulletin 767–32A0202, dated July 22, 2004;
and Boeing Alert Service Bulletin 767–
32A0199, Revision 2, dated May 26, 2005; as
applicable; to perform the actions that are
required by this AD, 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 Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207,
for a copy of this service information. You
may review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street, SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
16:05 Apr 06, 2006
Jkt 208001
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier Model DHC–8–400 series
airplanes. This AD requires replacing all
domed anchor nuts at all attachment
locations of the upper fuel access panels
of the center wing in the wet bay
location with new nuts. This AD results
from reported cases of corroded dome
anchor nuts at the attachment locations
of the upper surface of the fuel access
panel of the center wing. We are issuing
this AD to prevent corrosion or
perforation of domed anchor nuts,
which could result in arcing and
ignition of fuel vapor in the center wing
fuel tank during a lightning strike and
consequent explosion of the fuel tank.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
This AD becomes effective May
12, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of May 12, 2006.
DATES:
You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this AD.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
George Duckett, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, suite 410, Westbury, New York
11590; telephone (516) 228–7325; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Bombardier Model
DHC–8–400 series airplanes. That
NPRM was published in the Federal
Register on February 8, 2006 (71 FR
6411). That NPRM proposed to require
replacing all domed anchor nuts at all
attachment locations of the upper fuel
access panels of the center wing in the
wet bay location with new nuts.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the NPRM or on the
determination of the cost to the public.
Change to NPRM
We have revised the telephone
number in the FOR FURTHER INFORMATION
CONTACT paragraph.
E:\FR\FM\07APR1.SGM
07APR1
Federal Register / Vol. 71, No. 67 / Friday, April 7, 2006 / Rules and Regulations
Conclusion
We have carefully reviewed the
available data, and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
This AD will affect about 20 airplanes
of U.S. registry. The required actions
will take about 62 work hours per
airplane, at an average labor rate of $65
per work hour. Required parts will cost
about $300 per airplane. Based on these
figures, the estimated cost of the AD for
U.S. operators is $86,600, or $4,330 per
airplane.
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.
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 that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
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:
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
We have determined that this AD will
not have federalism implications under
by adding the following new
airworthiness directive (AD):
2006–07–16 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–14543.
Docket No. FAA–2006–23798;
Directorate Identifier 2005–NM–162–AD.
Effective Date
(a) This AD becomes effective May 12,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–400 series airplanes, certificated in
any category; serial numbers 4001, and 4003
through 4115 inclusive.
Unsafe Condition
(d) This AD results from reported cases of
corroded dome anchor nuts at the attachment
locations of the upper surface of the fuel
access panel of the center wing. We are
issuing this AD to prevent corrosion or
perforation of domed anchor nuts, which
could result in arcing and ignition of fuel
vapor in the center wing fuel tank during a
lightning strike and consequent explosion of
the fuel tank.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Replacement With Corrosion Resistant
Anchor Nuts
PART 39—AIRWORTHINESS
DIRECTIVES
Regulatory Findings
17695
I
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
(f) At the applicable time in Table 1 of this
AD, replace all domed anchor nuts at all
attachment locations of the upper fuel access
panels of the center wing in the wet bay
location with new, corrosion-resistant anchor
nuts. Do all the actions in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–57–10,
Revision ‘‘A,’’ dated March 14, 2005.
TABLE 1.—COMPLIANCE TIME
On which the inspection(s) specified in—
Do the replacement—
(1) 4108 through 4115 inclusive ........................
None .................................................................
(2) 4001, and 4003 through 4107 inclusive ......
wwhite on PROD1PC65 with RULES
For airplanes having serial number(s)—
Bombardier Service Bulletin 84–57–11, dated
February 25, 2005; or Revision ‘A,’ dated
March 9, 2005; have been done before the
effective date of this AD.
Bombardier Service Bulletin 84–57–12, dated
March 11, 2005, has been done before the
effective date of this AD.
Bombardier Service Bulletin 84–57–11, dated
February 25, 2005, or Revision ‘A,’ dated
March 9, 2005; or Bombardier Service Bulletin 84–57–12, dated March 11, 2005; has
not been done before the effective date of
this AD.
Within 48 months after the date of issuance of
the original standard Canadian airworthiness certificate or the date of issuance of
the original Canadian export certificate of
airworthiness, or within 2 months after the
effective date of this AD, whichever occurs
later.
Within 24 months after those inspections, or
within 2 months after the effective date of
this AD, whichever occurs later.
VerDate Aug<31>2005
16:05 Apr 06, 2006
Jkt 208001
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
Within 48 months after that inspection, or
within 2 months after the effective date of
this AD, whichever occurs later.
Within 3 months after the effective date of this
AD.
E:\FR\FM\07APR1.SGM
07APR1
17696
Federal Register / Vol. 71, No. 67 / Friday, April 7, 2006 / Rules and Regulations
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, New York Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(h) Canadian airworthiness directive CF–
2005–08R1, dated August 10, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
(i) You must use Bombardier Service
Bulletin 84–57–10, Revision ‘A,’ dated March
14, 2005, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5,
Canada, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_
locations.html.
Issued in Renton, Washington, on March
24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–3196 Filed 4–6–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23672; Directorate
Identifier 2005–NM–237–AD; Amendment
39–14544; AD 2006–07–17]
RIN 2120–AA64
wwhite on PROD1PC65 with RULES
Airworthiness Directives; Boeing
Model 727, 727C, 727–100, 727–100C,
and 727–200 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
VerDate Aug<31>2005
16:05 Apr 06, 2006
Jkt 208001
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing transport category airplanes.
This AD requires determining if the
terminal fittings of the spars of the
wings are made of 7079 aluminum alloy
material. For any positive finding, the
AD requires doing repetitive inspections
for cracks and corrosion of all exposed
surfaces of the terminal fitting bores;
doing repetitive inspections for cracks,
corrosion, and other surface defects, of
all exposed surfaces, including the
flanges, of the terminal fitting; applying
corrosion inhibiting compound to the
terminal fittings; and repairing or
replacing any cracked, corroded, or
defective part with a new part. This AD
also provides for an optional
terminating action for the repetitive
inspections. This AD results from
reports of cracking of the terminal
fittings of the spars of the wings. We are
issuing this AD to detect and correct
stress-corrosion cracking of the terminal
fittings, which could result in the failure
of one of the terminal fitting
connections. Such a failure, combined
with a similar failure of one of the other
three terminal fittings, could result in
the inability of the airplane structure to
carry fail-safe loads, which could result
in loss of structural integrity of the wing
attachment points.
DATES: This AD becomes effective May
12, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of May 12, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Daniel F. Kutz, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6456; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Boeing transport
category airplanes. That NPRM was
published in the Federal Register on
January 25, 2006 (71 FR 4069). That
NPRM proposed to require determining
if the terminal fittings of the spars of the
wings are made of 7079 aluminum alloy
material. For any positive finding, the
NPRM proposed to require doing
repetitive inspections for cracks and
corrosion of all exposed surfaces of the
terminal fitting bores; doing repetitive
inspections for cracks, corrosion, and
other surface defects, of all exposed
surfaces, including the flanges, of the
terminal fitting; applying corrosion
inhibiting compound to the terminal
fittings; and repairing or replacing any
cracked, corroded, or defective part with
a new part. The NPRM also proposed to
provide an optional terminating action
for the repetitive inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received. The
commenter, Boeing, supports the
NPRM.
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD as proposed.
Interim Action
This AD is considered to be interim
action. The inspection reports that are
required by this AD will enable the
manufacturer to obtain better insight
into the extent of the cracking and
corrosion of the terminal fittings of the
front and rear spars of the wings in the
fleet, and to develop additional action if
necessary to address the unsafe
condition. If additional action is
identified, we may consider further
rulemaking.
Costs of Compliance
There are about 302 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 157 airplanes
of U.S. registry. The determination of
forging number/material identification
will take about 4 work hours per
airplane, at an average labor rate of $65
E:\FR\FM\07APR1.SGM
07APR1
]]>Agencies
[Federal Register Volume 71, Number 67 (Friday, April 7, 2006)]
[Unknown Section]
[Pages 17694-17696]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-3196]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23798; Directorate Identifier 2005-NM-162-AD;
Amendment 39-14543; AD 2006-07-16]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier Model DHC-8-400 series airplanes. This AD requires
replacing all domed anchor nuts at all attachment locations of the
upper fuel access panels of the center wing in the wet bay location
with new nuts. This AD results from reported cases of corroded dome
anchor nuts at the attachment locations of the upper surface of the
fuel access panel of the center wing. We are issuing this AD to prevent
corrosion or perforation of domed anchor nuts, which could result in
arcing and ignition of fuel vapor in the center wing fuel tank during a
lightning strike and consequent explosion of the fuel tank.
DATES: This AD becomes effective May 12, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of May 12, 2006.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: George Duckett, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New
York 11590; telephone (516) 228-7325; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Bombardier
Model DHC-8-400 series airplanes. That NPRM was published in the
Federal Register on February 8, 2006 (71 FR 6411). That NPRM proposed
to require replacing all domed anchor nuts at all attachment locations
of the upper fuel access panels of the center wing in the wet bay
location with new nuts.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the NPRM or on the
determination of the cost to the public.
Change to NPRM
We have revised the telephone number in the FOR FURTHER INFORMATION
CONTACT paragraph.
[[Page 17695]]
Conclusion
We have carefully reviewed the available data, and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
This AD will affect about 20 airplanes of U.S. registry. The
required actions will take about 62 work hours per airplane, at an
average labor rate of $65 per work hour. Required parts will cost about
$300 per airplane. Based on these figures, the estimated cost of the AD
for U.S. operators is $86,600, or $4,330 per airplane.
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 have 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 that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2006-07-16 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-14543. Docket No. FAA-2006-23798; Directorate Identifier 2005-NM-
162-AD.
Effective Date
(a) This AD becomes effective May 12, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400 series
airplanes, certificated in any category; serial numbers 4001, and
4003 through 4115 inclusive.
Unsafe Condition
(d) This AD results from reported cases of corroded dome anchor
nuts at the attachment locations of the upper surface of the fuel
access panel of the center wing. We are issuing this AD to prevent
corrosion or perforation of domed anchor nuts, which could result in
arcing and ignition of fuel vapor in the center wing fuel tank
during a lightning strike and consequent explosion of the fuel tank.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Replacement With Corrosion Resistant Anchor Nuts
(f) At the applicable time in Table 1 of this AD, replace all
domed anchor nuts at all attachment locations of the upper fuel
access panels of the center wing in the wet bay location with new,
corrosion-resistant anchor nuts. Do all the actions in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
84-57-10, Revision ``A,'' dated March 14, 2005.
Table 1.--Compliance Time
------------------------------------------------------------------------
On which the
For airplanes having serial inspection(s) Do the
number(s)-- specified in-- replacement--
------------------------------------------------------------------------
(1) 4108 through 4115 inclusive. None.............. Within 48 months
after the date of
issuance of the
original standard
Canadian
airworthiness
certificate or
the date of
issuance of the
original Canadian
export
certificate of
airworthiness, or
within 2 months
after the
effective date of
this AD,
whichever occurs
later.
(2) 4001, and 4003 through 4107 Bombardier Service Within 24 months
inclusive. Bulletin 84-57- after those
11, dated inspections, or
February 25, within 2 months
2005; or Revision after the
`A,' dated March effective date of
9, 2005; have this AD,
been done before whichever occurs
the effective later.
date of this AD.
Bombardier Service Within 48 months
Bulletin 84-57- after that
12, dated March inspection, or
11, 2005, has within 2 months
been done before after the
the effective effective date of
date of this AD. this AD,
whichever occurs
later.
Bombardier Service Within 3 months
Bulletin 84-57- after the
11, dated effective date of
February 25, this AD.
2005, or Revision
`A,' dated March
9, 2005; or
Bombardier
Service Bulletin
84-57-12, dated
March 11, 2005;
has not been done
before the
effective date of
this AD.
------------------------------------------------------------------------
[[Page 17696]]
Alternative Methods of Compliance (AMOCs)
(g)(1) The Manager, New York Aircraft Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(h) Canadian airworthiness directive CF-2005-08R1, dated August
10, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(i) You must use Bombardier Service Bulletin 84-57-10, Revision
`A,' dated March 14, 2005, to perform the actions that are required
by this AD, unless the AD specifies otherwise. The Director of the
Federal Register approved the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123
Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for a copy of
this service information. You may review copies at the Docket
Management Facility, U.S. Department of Transportation, 400 Seventh
Street, SW., Room PL-401, Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_
regulations/ibr_ locations. html.
Issued in Renton, Washington, on March 24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-3196 Filed 4-6-06; 8:45 am]
BILLING CODE 4910-13-P
