Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -106 Airplanes; and Model DHC-8-200 and -300 Series Airplanes, 6408-6411 [E6-1683]
Download as PDF
<![CDATA[
6408
Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules
TABLE 3.—REVISION 1 OF SERVICE BULLETINS—Continued
For model—
Boeing service bulletin—
(3) 747–400 and 747–400F series airplanes ...........................................
Note 1: Each service bulletin identified in
table 3 of this AD refers to Rockwell Collins
Service Bulletins IDS–7000–31–49, IDS–
7000–31–50, or IDS–7000–31–51; all dated
June 28, 2004; as applicable; as an additional
747–31A2352, Revision 1, dated March 17, 2005.
source of service information for installing
the new IDS software.
(i) Installing new IDS software before the
effective date of this AD in accordance with
the applicable service bulletin in table 4 of
this AD, is acceptable for compliance with
the requirements of paragraph (h) of this AD.
TABLE 4.—ORIGINAL SERVICE BULLETINS
For model—
Boeing service bulletin—
(1) 747–400, 747–400D, and 747–400F series airplanes .......................
(2) 747–400 and 747–400F series airplanes ...........................................
(3) 747–400 and 747–400F series airplanes ...........................................
Removal of Pin Ground Wires
(j) For airplanes on which FR–HiTEMP fuel
pumps have been incorporated in accordance
with Boeing Service Bulletin 747–28–2258,
dated December 19, 2003; or Revision 1,
dated August 11, 2005: Before further flight
after installing the new IDS software required
by paragraph (h) of this AD, remove the G13
pin ground wires of the wire integration unit
on the E2–6 electronic shelf of the left,
center, and right electronics interface units,
that correspond to the connector locations in
table 5 of this AD, in accordance with a
method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA.
Chapter 20–41–03 of the Boeing 747–400
Aircraft Maintenance Manual is one
approved method.
TABLE 5.—CONNECTOR LOCATION
Connector
DM7353CA ................
DM7352CA ................
DM7351CA ................
Location
Left EIU.
Center EIU.
Right EIU.
AFM Revision
(k) Concurrently with the requirements of
paragraph (h) of this AD, revise the
Limitations section of the AFM to include the
following (this may be done by inserting a
copy of this AD into the AFM):
rmajette on PROD1PC67 with PROPOSALS1
Certification Limitations
Center Wing Tank (CWT): The CWT fuel
quantity indication system must be operative
to dispatch with CWT mission fuel.
The CWT must contain a minimum of
17,000 pounds (7,700 kilograms) prior to
engine start, if the CWT override/jettison
pumps are to be selected ON during takeoff.
If the FUEL LOW CTR L or R message is
displayed both CWT override/jettison pumps
must be selected OFF.
If the FUEL PRESS CTR L or R message is
displayed, the corresponding CWT override/
jettison pump must be selected OFF.
Horizontal Stabilizer Tank (HST): The
following additional limitations must be
followed if the HST is fueled and used:
VerDate Aug<31>2005
15:24 Feb 07, 2006
Jkt 208001
747–31A2351, dated September 3, 2004.
747–31A2350, dated September 3, 2004.
747–31A2352, dated September 3, 2004.
The HST fuel quantity indication system
must be operative to dispatch with HST
mission fuel.
If the FUEL PMP STB L or R message is
displayed while on the ground both HST
pumps must be selected OFF.
If the FUEL LOW STAB L or R message is
displayed in flight the corresponding HST
pump must be selected OFF.
If the FUEL PRESS STAB L or R is
displayed the corresponding HST pump must
be selected OFF.
The remaining fuel in the HST must be
considered unusable, and the effects of that
unusable fuel on balance (CG) must be
considered.
Warning: Do not reset a tripped fuel pump
circuit breaker.
Defueling: Prior to defueling any fuel tanks,
perform a lamp test of the respective Fuel
Pump Low Pressure indication lights. When
defueling, the Fuel Pump Low Pressure
indication lights must be monitored and the
fuel pumps positioned to OFF at the first
indication of fuel pump low pressure. When
defueling with passengers on board, fuel
pump switches must be selected OFF at or
above approximately 7,000 pounds (3,200
kilograms) for the CWT, 3,000 pounds (1,400
kilograms) for main tanks, and 2,100 pounds
(1,000 kilograms) for the HST.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, Seattle ACO, 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.
Issued in Renton, Washington, on January
30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–1682 Filed 2–7–06; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23820; Directorate
Identifier 2005–NM–249–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–102, –103, and –106
Airplanes; and Model DHC–8–200 and
–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to revise
an existing airworthiness directive (AD)
that applies to certain Bombardier
Model DHC–8–102, –103, and –106
airplanes; and Model DHC–8–200 and
–300 series airplanes. The existing AD
currently requires performing a onetime inspection to detect chafing of
electrical wires in the cable trough
below the cabin floor; repairing, if
necessary; installing additional tiemounts and tie-wraps; applying sealant
to rivet heads; and modifying electrical
wires in certain sections. This proposed
AD would, for certain airplanes,
eliminate the requirement to modify
electrical wires in certain sections. This
proposed AD results from a report
indicating that the modification of
electrical wires does not need to be
done on certain airplanes subject to the
existing AD. We are proposing this AD
to prevent chafing of electrical wires,
which could result in an uncommanded
shutdown of an engine during flight.
DATES: We must receive comments on
this proposed AD by March 10, 2006.
E:\FR\FM\08FEP1.SGM
08FEP1
Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules
Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT:
Douglas G. Wagner, Aerospace Engineer,
Systems and Flight Test Branch, ANE–
172, New York Aircraft Certification
Office, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, New York 11590;
telephone (516) 228–7306; fax (516)
794–5531.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
rmajette on PROD1PC67 with PROPOSALS1
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘Docket No. FAA–2006–23820;
Directorate Identifier 2005–NM–249–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in a docket, including the
name of the individual who sent the
comment (or signed the comment on
behalf of an association, business, labor
union, etc.). You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
VerDate Aug<31>2005
15:24 Feb 07, 2006
Jkt 208001
2000 (65 FR 19477–78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
On January 29, 2004, we issued AD
2004–03–15, amendment 39–13459 (69
FR 7111, February 13, 2004), for certain
Bombardier Model DHC–8–102, –103,
–106, –201, –202, –301, –311, and –315
airplanes. That AD requires a one-time
inspection to detect chafing of electrical
wires in the cable trough below the
cabin floor; repair, if necessary;
installation of additional tie-mounts and
tie-wraps; application of sealant to rivet
heads; and modification of the electrical
wires in certain sections. That AD
resulted from a report of an
uncommanded engine shutdown during
flight. We issued that AD to prevent
chafing of electrical wires, which could
result in an uncommanded shutdown of
an engine during flight.
Actions Since Existing AD Was Issued
Paragraph (b) of AD 2004–03–15
requires all airplanes subject to the AD
to modify the electrical wires in the
cable trough below the cabin floor at
Sections X510.00 to X580.50, in
accordance with Bombardier Service
Bulletin 8–53–80, Revision ‘A,’ dated
July 25, 2000. Since we issued AD
2004–03–15, we have received a report
indicating that Bombardier Model DHC–
8–300 series airplanes should not be
required to do this modification.
We have reviewed Canadian
airworthiness directive CF–1998–08R2,
dated July 12, 2000, which AD 2004–
03–15 refers to as the parallel Canadian
airworthiness directive. Canadian
airworthiness directive CF–1998–08R2
identifies Model DHC–8–300 series
airplanes as being subject only to
Bombardier Service Bulletin S.B. 8–53–
66, dated March 27, 1998, not to
Bombardier Service Bulletin 8–53–80,
Revision ‘A.’ (Paragraph (a) of AD 2004–
03–15 refers to Bombardier Service
Bulletin S.B. 8–53–66 as the appropriate
source of service information for the
actions required by that paragraph.)
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
6409
FAA’s Determination and Requirements
of the Proposed AD
These airplane models are
manufactured in Canada and are type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, Transport
Canada Civil Aviation (TCCA), which is
the airworthiness authority for Canada,
has kept the FAA informed of the
situation described above. We have
examined TCCA’s findings, evaluated
all pertinent information, and
determined that we need to issue an AD
for airplanes of this type design that are
certificated for operation in the United
States.
This proposed AD would revise AD
2004–03–15 and would retain the
requirements of the existing AD. This
proposed AD would eliminate the
requirement to modify electrical wires
in certain sections on Model DHC–8–
300 series airplanes. The actions would
be required to be done in accordance
with the service information specified
in the existing AD, except as discussed
under ‘‘Difference Between This
Proposed AD and Service Bulletin’’ in
the notice of proposed rulemaking for
AD 2004–03–15.
Changes to Existing AD
This proposed AD would retain all
requirements of AD 2004–03–15. Since
AD 2004–03–15 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2004–03–15
paragraph (a) ............
paragraph (b) ............
Corresponding requirement in this
proposed AD
paragraph (f).
paragraph (g).
Also, we have revised the range of
airplane serial numbers (S/Ns) stated in
paragraphs (f)(1) and (f)(2) of this
proposed AD. Paragraphs (a)(1) and
(a)(2) of AD 2004–03–15 specify the
compliance times for inspections in
accordance with Bombardier Service
Bulletin 8–53–66, as required by
paragraph (a) of that AD. Paragraph
(a)(1) of AD 2004–03–15 states the
compliance time for S/Ns 3 through 519
inclusive (excluding S/N 462).
Paragraph (a)(2) states the compliance
E:\FR\FM\08FEP1.SGM
08FEP1
6410
Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules
time for S/Ns 520 through 540 inclusive.
We have determined that the airplane
having S/N 519 was incorrectly
included in paragraph (a)(1) of AD
2004–03–15. That airplane is a Model
DHC–8–300 series airplane and should
be subject to the compliance time in
paragraph (a)(2) of AD 2004–03–15.
Therefore, we have revised paragraphs
(f)(1) and (f)(2) of this proposed AD to
move S/N 519 into paragraph (f)(2) of
this proposed AD. (This change results
in a slight extension of the compliance
time for the airplane having S/N 519.)
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
rmajette on PROD1PC67 with PROPOSALS1
Costs of Compliance
This new AD adds no new costs to
affected operators; in fact, it reduces the
costs for some airplanes that are not
subject to the modification of certain
wiring.
We estimate that 173 airplanes of U.S.
registry will be subject to the inspection,
installation of additional tie-mounts and
tie-wraps, and application of sealant to
rivet heads that are currently required
by AD 2004–03–15. These actions take
between 80 and 100 work hours per
airplane, at an average labor rate of $65
per work hour. Required parts are
provided by the manufacturer at no cost
to the operator. Based on these figures,
the estimated cost of these actions on
U.S. operators is between $899,600 and
$1,124,500, or between $5,200 and
$6,500 per airplane.
We estimate that 103 airplanes of U.S.
registry are subject to the modification
of certain wiring that is currently
required by AD 2004–03–15. This action
takes approximately 10 work hours per
airplane, at an average labor rate of $65
per work hour. Required parts are
provided by the manufacturer at no cost
to the operator. Based on these figures,
the estimated cost of the modification
on U.S. operators is $66,950, or $650 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,
VerDate Aug<31>2005
15:24 Feb 07, 2006
Jkt 208001
‘‘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
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. 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, 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 Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13459 (69
FR 7111, February 13, 2004) and adding
the following new airworthiness
directive (AD):
Bombardier, Inc. (Formerly de Havilland,
Inc.): Docket No. FAA–2006–23820;
Directorate Identifier 2005–NM–249–AD.
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
Comments Due Date
(a) The FAA must receive comments on
this AD action by March 10, 2006.
Affected ADs
(b) This AD revises AD 2004–03–15.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–102, –103, and –106 airplanes; and
Model DHC–8–200 and DHC–8–300 series
airplanes; certificated in any category serial
numbers 3 through 540 inclusive, excluding
serial number 462.
Unsafe Condition
(d) This AD results from a report indicating
that the modification of electrical wires does
not need to be done on certain airplanes
subject to the existing AD. We are issuing
this AD to prevent chafing of electrical wires,
which could result in an uncommanded
shutdown of an engine during flight.
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.
Requirements of AD 2004–03–15
One-Time Inspection, Corrective Action, and
Modification
(f) Perform a one-time general visual
inspection to detect chafing of electrical
wires in the cable trough below the cabin
floor; install additional tie-mounts and tiewraps; and apply sealant to rivet heads
(reference Bombardier Modification 8/2705);
in accordance with Bombardier Service
Bulletin S.B. 8–53–66, dated March 27, 1998,
at the time specified in paragraph (f)(1) or
(f)(2) of this AD, as applicable. If any chafing
is detected during the inspection required by
this paragraph, prior to further flight, repair
in accordance with the service bulletin.
Note 1: For the purposes of this AD, a
general visual inspection is defined as: ‘‘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 enhance visual
access to all exposed 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.’’
(1) For airplanes having serial numbers 3
through 518 inclusive, excluding serial
number 462: Inspect within 36 months after
October 27, 1998 (the effective date of AD
98–20–14, amendment 39–10781).
(2) For airplanes having serial numbers 519
through 540 inclusive: Inspect within 36
months after November 10, 1999 (the
effective date of AD 99–21–09, amendment
39–11352, which superseded AD 98–20–14),
or at the next ‘‘C’’ check, whichever occurs
first.
E:\FR\FM\08FEP1.SGM
08FEP1
Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules
Modification
(g) For Model DHC–8–102, –103, and –106
airplanes; and Model DHC–8–200 series
airplanes: Within 36 months after March 19,
2004 (the effective date of AD 2004–03–15),
modify the electrical wires in the cable
trough below the cabin floor at Sections
X510.00 to X580.50 (including performing a
general visual inspection and any applicable
repair), in accordance with Part III,
paragraphs 1 through 9 and 12 through 20,
of the Accomplishment Instructions of
Bombardier Service Bulletin 8–53–80,
Revision ‘‘A,’’ dated July 25, 2000. Any
applicable repair must be done before further
flight. Accomplishment of these actions
before March 19, 2004, in accordance with
Bombardier Service Bulletin 8–53–80, dated
December 22, 1999, is considered acceptable
for compliance with the actions required by
this paragraph.
Alternative Methods of Compliance (AMOCs)
(h)(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
(i) Canadian airworthiness directive CF–
1998–08R2, dated July 10, 2000, also
addresses the subject of this AD.
Issued in Renton, Washington, on
January 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–1683 Filed 2–7–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Comments Invited
[Docket No. FAA–2006–23798; Directorate
Identifier 2005–NM–162–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking.
rmajette on PROD1PC67 with PROPOSALS1
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model DHC–8–400
series airplanes. This proposed AD
would 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
VerDate Aug<31>2005
19:52 Feb 07, 2006
new nuts. This proposed 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
proposing 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: We must receive comments on
this proposed AD by March 10, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to http:
//dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this proposed 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) 228–7525; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Jkt 208001
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2006–23798; Directorate
Identifier 2005–NM–162–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
6411
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, notified us that an
unsafe condition may exist on certain
Bombardier Model DHC–8–400 series
airplanes. TCCA advises that, during
‘‘2C’’ checks, there have been a number
of reported cases of corrosion of dome
anchor nuts at the attachment locations
of the upper surface of the fuel access
panel of the center wing. In some cases,
the dome anchor nuts were severely
corroded and perforated. This
condition, if not corrected, 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.
Relevant Service Information
Bombardier has issued Service
Bulletin 84–57–10, Revision ‘‘A,’’ dated
March 14, 2005. The service bulletin
describes procedures for 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, corrosion-resistant
anchor nuts. Accomplishing the actions
specified in the service information is
intended to adequately address the
unsafe condition.
The TCCA mandated the service
information described previously, or
Bombardier Service Bulletin 84–57–11,
E:\FR\FM\08FEP1.SGM
08FEP1
]]>Agencies
[Federal Register Volume 71, Number 26 (Wednesday, February 8, 2006)]
[Proposed Rules]
[Pages 6408-6411]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-1683]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23820; Directorate Identifier 2005-NM-249-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -
106 Airplanes; and Model DHC-8-200 and -300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to revise an existing airworthiness directive
(AD) that applies to certain Bombardier Model DHC-8-102, -103, and -106
airplanes; and Model DHC-8-200 and -300 series airplanes. The existing
AD currently requires performing a one-time inspection to detect
chafing of electrical wires in the cable trough below the cabin floor;
repairing, if necessary; installing additional tie-mounts and tie-
wraps; applying sealant to rivet heads; and modifying electrical wires
in certain sections. This proposed AD would, for certain airplanes,
eliminate the requirement to modify electrical wires in certain
sections. This proposed AD results from a report indicating that the
modification of electrical wires does not need to be done on certain
airplanes subject to the existing AD. We are proposing this AD to
prevent chafing of electrical wires, which could result in an
uncommanded shutdown of an engine during flight.
DATES: We must receive comments on this proposed AD by March 10, 2006.
[[Page 6409]]
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Douglas G. Wagner, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, New York Aircraft
Certification Office, FAA, 1600 Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228-7306; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2006-23820; Directorate Identifier 2005-NM-249-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in a docket,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the 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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
On January 29, 2004, we issued AD 2004-03-15, amendment 39-13459
(69 FR 7111, February 13, 2004), for certain Bombardier Model DHC-8-
102, -103, -106, -201, -202, -301, -311, and -315 airplanes. That AD
requires a one-time inspection to detect chafing of electrical wires in
the cable trough below the cabin floor; repair, if necessary;
installation of additional tie-mounts and tie-wraps; application of
sealant to rivet heads; and modification of the electrical wires in
certain sections. That AD resulted from a report of an uncommanded
engine shutdown during flight. We issued that AD to prevent chafing of
electrical wires, which could result in an uncommanded shutdown of an
engine during flight.
Actions Since Existing AD Was Issued
Paragraph (b) of AD 2004-03-15 requires all airplanes subject to
the AD to modify the electrical wires in the cable trough below the
cabin floor at Sections X510.00 to X580.50, in accordance with
Bombardier Service Bulletin 8-53-80, Revision `A,' dated July 25, 2000.
Since we issued AD 2004-03-15, we have received a report indicating
that Bombardier Model DHC-8-300 series airplanes should not be required
to do this modification.
We have reviewed Canadian airworthiness directive CF-1998-08R2,
dated July 12, 2000, which AD 2004-03-15 refers to as the parallel
Canadian airworthiness directive. Canadian airworthiness directive CF-
1998-08R2 identifies Model DHC-8-300 series airplanes as being subject
only to Bombardier Service Bulletin S.B. 8-53-66, dated March 27, 1998,
not to Bombardier Service Bulletin 8-53-80, Revision `A.' (Paragraph
(a) of AD 2004-03-15 refers to Bombardier Service Bulletin S.B. 8-53-66
as the appropriate source of service information for the actions
required by that paragraph.)
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in Canada and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, Transport Canada Civil Aviation
(TCCA), which is the airworthiness authority for Canada, has kept the
FAA informed of the situation described above. We have examined TCCA's
findings, evaluated all pertinent information, and determined that we
need to issue an AD for airplanes of this type design that are
certificated for operation in the United States.
This proposed AD would revise AD 2004-03-15 and would retain the
requirements of the existing AD. This proposed AD would eliminate the
requirement to modify electrical wires in certain sections on Model
DHC-8-300 series airplanes. The actions would be required to be done in
accordance with the service information specified in the existing AD,
except as discussed under ``Difference Between This Proposed AD and
Service Bulletin'' in the notice of proposed rulemaking for AD 2004-03-
15.
Changes to Existing AD
This proposed AD would retain all requirements of AD 2004-03-15.
Since AD 2004-03-15 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2004-03-15 this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
------------------------------------------------------------------------
Also, we have revised the range of airplane serial numbers (S/Ns)
stated in paragraphs (f)(1) and (f)(2) of this proposed AD. Paragraphs
(a)(1) and (a)(2) of AD 2004-03-15 specify the compliance times for
inspections in accordance with Bombardier Service Bulletin 8-53-66, as
required by paragraph (a) of that AD. Paragraph (a)(1) of AD 2004-03-15
states the compliance time for S/Ns 3 through 519 inclusive (excluding
S/N 462). Paragraph (a)(2) states the compliance
[[Page 6410]]
time for S/Ns 520 through 540 inclusive. We have determined that the
airplane having S/N 519 was incorrectly included in paragraph (a)(1) of
AD 2004-03-15. That airplane is a Model DHC-8-300 series airplane and
should be subject to the compliance time in paragraph (a)(2) of AD
2004-03-15. Therefore, we have revised paragraphs (f)(1) and (f)(2) of
this proposed AD to move S/N 519 into paragraph (f)(2) of this proposed
AD. (This change results in a slight extension of the compliance time
for the airplane having S/N 519.)
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Costs of Compliance
This new AD adds no new costs to affected operators; in fact, it
reduces the costs for some airplanes that are not subject to the
modification of certain wiring.
We estimate that 173 airplanes of U.S. registry will be subject to
the inspection, installation of additional tie-mounts and tie-wraps,
and application of sealant to rivet heads that are currently required
by AD 2004-03-15. These actions take between 80 and 100 work hours per
airplane, at an average labor rate of $65 per work hour. Required parts
are provided by the manufacturer at no cost to the operator. Based on
these figures, the estimated cost of these actions on U.S. operators is
between $899,600 and $1,124,500, or between $5,200 and $6,500 per
airplane.
We estimate that 103 airplanes of U.S. registry are subject to the
modification of certain wiring that is currently required by AD 2004-
03-15. This action takes approximately 10 work hours per airplane, at
an average labor rate of $65 per work hour. Required parts are provided
by the manufacturer at no cost to the operator. Based on these figures,
the estimated cost of the modification on U.S. operators is $66,950, or
$650 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. 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, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-13459 (69 FR 7111, February 13, 2004) and adding
the following new airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2006-
23820; Directorate Identifier 2005-NM-249-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by March 10,
2006.
Affected ADs
(b) This AD revises AD 2004-03-15.
Applicability
(c) This AD applies to Bombardier Model DHC-8-102, -103, and -
106 airplanes; and Model DHC-8-200 and DHC-8-300 series airplanes;
certificated in any category serial numbers 3 through 540 inclusive,
excluding serial number 462.
Unsafe Condition
(d) This AD results from a report indicating that the
modification of electrical wires does not need to be done on certain
airplanes subject to the existing AD. We are issuing this AD to
prevent chafing of electrical wires, which could result in an
uncommanded shutdown of an engine during flight.
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.
Requirements of AD 2004-03-15
One-Time Inspection, Corrective Action, and Modification
(f) Perform a one-time general visual inspection to detect
chafing of electrical wires in the cable trough below the cabin
floor; install additional tie-mounts and tie-wraps; and apply
sealant to rivet heads (reference Bombardier Modification 8/2705);
in accordance with Bombardier Service Bulletin S.B. 8-53-66, dated
March 27, 1998, at the time specified in paragraph (f)(1) or (f)(2)
of this AD, as applicable. If any chafing is detected during the
inspection required by this paragraph, prior to further flight,
repair in accordance with the service bulletin.
Note 1: For the purposes of this AD, a general visual inspection
is defined as: ``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 enhance visual access to all exposed 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.''
(1) For airplanes having serial numbers 3 through 518 inclusive,
excluding serial number 462: Inspect within 36 months after October
27, 1998 (the effective date of AD 98-20-14, amendment 39-10781).
(2) For airplanes having serial numbers 519 through 540
inclusive: Inspect within 36 months after November 10, 1999 (the
effective date of AD 99-21-09, amendment 39-11352, which superseded
AD 98-20-14), or at the next ``C'' check, whichever occurs first.
[[Page 6411]]
Modification
(g) For Model DHC-8-102, -103, and -106 airplanes; and Model
DHC-8-200 series airplanes: Within 36 months after March 19, 2004
(the effective date of AD 2004-03-15), modify the electrical wires
in the cable trough below the cabin floor at Sections X510.00 to
X580.50 (including performing a general visual inspection and any
applicable repair), in accordance with Part III, paragraphs 1
through 9 and 12 through 20, of the Accomplishment Instructions of
Bombardier Service Bulletin 8-53-80, Revision ``A,'' dated July 25,
2000. Any applicable repair must be done before further flight.
Accomplishment of these actions before March 19, 2004, in accordance
with Bombardier Service Bulletin 8-53-80, dated December 22, 1999,
is considered acceptable for compliance with the actions required by
this paragraph.
Alternative Methods of Compliance (AMOCs)
(h)(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
(i) Canadian airworthiness directive CF-1998-08R2, dated July
10, 2000, also addresses the subject of this AD.
Issued in Renton, Washington, on January 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-1683 Filed 2-7-06; 8:45 am]
BILLING CODE 4910-13-P
