Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes, 5078-5081 [05-1808]
Download as PDF
<![CDATA[
5078
Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules
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. 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 FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Empresa Brasileira de Aeronautica S.A.
(EMBRAER): Docket No. FAA–2005–
20223; Directorate Identifier 2004–NM–
193–AD.
VerDate jul<14>2003
14:57 Jan 31, 2005
Jkt 205001
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
March 3, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model EMB–135 and
–145 series airplanes, certificated in any
category; as listed in EMBRAER Service
Bulletin 145–32–0091, Change 01, dated July
1, 2004.
Unsafe Condition
(d) This AD was prompted by a report of
a fractured axle of the trailing arm of the
main landing gear (MLG) due to corrosion of
the axle. We are issuing this AD to prevent
a broken trailing arm and consequent failure
of the MLG, which could lead to loss of
control and damage to the airplane during
take-off or landing.
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.
Inspection
(f) Within 600 flight hours or 180 days after
the effective date of this AD, whichever
occurs first, perform a detailed inspection for
surface bruising of the MLG trailing arms and
integrity of the MLG pivot axle sealant; in
accordance with the Accomplishment
Instructions of EMBRAER Service Bulletin
145–32–0091, Change 01, dated July 1, 2004.
If no sign of sealant failure or bruising of the
trailing arm is found, repeat the inspection
thereafter at intervals not to exceed 5,500
flight hours or 24 months, whichever occurs
first, until paragraph (g)(3) of this AD has
been accomplished.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Corrective/Terminating Actions
(g) If any sign of sealant failure or bruising
of either trailing arm surface is found, prior
to further flight, do paragraphs (g)(1), (g)(2)
and (g)(3) of this AD. Do the actions in
accordance with EMBRAER Service Bulletin
145–32–0091, Change 01, dated July 1, 2004.
Accomplishment of paragraphs (g)(2) and
(g)(3) of this AD ends the repetitive
inspections required by paragraph (f) of this
AD.
(1) Repair any bruising of the trailing arm
surface.
(2) Replace the MLG cardan with a new,
improved cardan.
(3) Perform a detailed inspection for
corrosion of the internal surface of the
trailing arm pivot axle.
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
(i) If no corrosion is found, apply
protective paint and corrosion inhibitors.
(ii) If corrosion is found, replace the pivot
axle with a new pivot axle and apply
corrosion inhibitors.
Note 2: EMBRAER Service Bulletin 145–
32–0091, Change 01, dated July 1, 2004,
refers to Embraer Liebherr Equipamentos do
Brasil S.A. (ELEB) Service Bulletin 2309–
2002–32–04, Revision 01, dated May 24,
2004, as an additional source of service
information for the inspection and repair of
the MLG components. The ELEB service
bulletin is included within the EMBRAER
service bulletin.
Actions Accomplished According to
Previous Issue of Service Bulletin
(h) Actions accomplished before the
effective date of this AD according to
EMBRAER Service Bulletin 145–32–0091,
dated February 19, 2004, are considered
acceptable for compliance with the
corresponding actions specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(i) 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.
Related Information
(j) Brazilian airworthiness directive 2004–
08–02, dated September 3, 2004, also
addresses the subject of this AD.
Issued in Renton, Washington, on January
21, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–1807 Filed 1–31–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20222; Directorate
Identifier 2004–NM–230–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–102, –103, –106, –201,
–202, –301, –311, and –315 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model DHC–8–102,
–103, –106, –201, –202, –301, –311, and
–315 airplanes. The subject of this
proposed AD is the pilot’s static system.
This proposed AD would require
E:\FR\FM\01FEP1.SGM
01FEP1
Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules
revising the airplane flight manual to
include applicable procedures to follow
when the flightcrew receives abnormal
indications of airspeed, altitude, or
vertical airspeed. This proposed AD
would also require modifying the static
system. This proposed AD is prompted
by a report of a leak in the static
pressure system, which could result in
loss of the static systems and
consequent erroneous data displayed on
the pilot’s flight instruments. We are
proposing this AD to advise the
flightcrew of applicable procedures in
the event of abnormal indications of
airspeed, altitude, or vertical airspeed;
and to prevent leaks in the static system,
which could result in the loss of critical
flight information that could result in
reduced controllability of the airplane
or controlled flight into terrain.
DATES: We must receive comments on
this proposed AD by March 3, 2005.
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.
• By 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.
For service information identified in
this proposed AD, contact Bombardier,
Inc., Bombardier Regional Aircraft
Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada.
You can examine the contents of this
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., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20222; the directorate identifier for this
docket is 2004–NM–230–AD.
FOR FURTHER INFORMATION CONTACT: Ezra
Sasson, Aerospace Engineer, Systems
and Flight Test Branch, ANE–172, FAA,
New York Aircraft Certification Office,
1600 Stewart Avenue, suite 410,
Westbury, New York 11590; telephone
(516) 228–7320; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
VerDate jul<14>2003
14:57 Jan 31, 2005
Jkt 205001
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 under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20222; Directorate Identifier
2004–NM–230–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 submitted 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 our docket
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 can
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can 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 DMS
receives them.
Discussion
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, notified the FAA
that an unsafe condition may exist on
certain Bombardier Model DHC–8–102,
–103, –106, –201, –202, –301, –311, and
–315 airplanes. TCCA advises that an
investigation of an incident involving
erroneous data displayed on the pilot’s
flight instruments has revealed that a
leak in the pilot’s side static pressure
system, downstream of the alternate
selector valve, could result in the loss of
both the pilot’s normal and alternate
static systems. This condition, if not
corrected, could result in the display of
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
5079
abnormal indications of airspeed,
altitude, or vertical airspeed due to
leaks in the static system and prolonged
loss of critical flight information that
could result in reduced controllability
of the airplane or controlled flight into
terrain.
Relevant Service Information
Bombardier has issued Service
Bulletin 8–34–221, Revision ‘A,’ dated
September 15, 2003. The service
bulletin describes procedures to modify
the pilot’s side static system to prevent
leaks in the system. For certain
airplanes the modification provides
increased independence of the static
pressure source for the pilot’s primary
and standby flight instruments, and for
certain other airplanes the modification
corrects the length of the static system
hose.
TCCA mandated the service bulletin
and issued Canadian airworthiness
directive CF–2003–25, dated October
10, 2003, to ensure the continued
airworthiness of these airplanes in
Canada.
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, TCCA 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 products of this
type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to
provide procedures to the flightcrew in
the event of abnormal indications of
airspeed, altitude, or vertical airspeed;
and to prevent leaks in the static system,
which could result in the loss of critical
flight information that could result in
reduced controllability of the airplane
or controlled flight into terrain. This AD
requires accomplishing the actions
specified in the service information
described previously, except as
discussed under ‘‘Differences Between
the Proposed AD and Canadian
Airworthiness Directive.’’
Differences Between the Proposed AD
and Canadian Airworthiness Directive
This proposed AD advises revising
the applicable de Havilland Dash 8
airplane flight manual to incorporate the
text specified in paragraph (f) of this
E:\FR\FM\01FEP1.SGM
01FEP1
5080
Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules
proposed AD. The Canadian AD does
not include such a requirement. In
Canada, operators are mandated to use
the latest flight manual and therefore,
TCCA is not required to issue an AD to
require flight manual revisions.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Average labor
rate per hour
Work hours
Revise AFM ........................
Modify static system ...........
1
2
$65
65
Cost per
airplane
Parts
None ...................................
100–200 ..............................
$65
230–330
Number of
U.S.-registered
airplanes
181
181
Fleet cost
$11,765
41,630–59,730
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
Compliance
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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.
This rulemaking is promulgated
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
proposed AD.
Air transportation, Aircraft, Aviation
safety, Safety.
(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.
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. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
VerDate jul<14>2003
14:57 Jan 31, 2005
Jkt 205001
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Bombardier, Inc. (Formerly de Havilland,
Inc.): Docket No. FAA–2005–20222;
Directorate Identifier 2004–NM–230–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
March 3, 2005.
Affected ADs
Applicability
(c) This AD applies to Bombardier Model
DHC–8–102, –103, –106, –201, –202, –301,
–311, and –315 airplanes, certificated in any
category; serial numbers 003 through 598
inclusive.
Unsafe Condition
(d) This AD was prompted by a report of
a leak in the static pressure system, which
could result in loss of the static systems and
consequent erroneous data displayed on the
pilot’s flight instruments. The subject of this
AD is the pilot’s static system. We are issuing
this AD to advise the flightcrew of applicable
procedures in the event of abnormal
indications of airspeed, altitude, or vertical
airspeed; and to prevent leaks in the static
system, which could result in the loss of
critical flight information that could result in
reduced controllability of the airplane or
controlled flight into terrain.
Frm 00017
(f) Within 10 days after the effective date
of this AD, revise the Normal and Abnormal
Procedures sections of the applicable de
Havilland Dash 8 flight manual to include
the following statement in paragraph 4.11.1
of 4.11 Pitot—Static and Stall Warning
System Failures. This may be done by
inserting a copy of this AD in the applicable
flight manual.
‘‘4.11.1 ABNORMAL INDICATIONS OF
AIRSPEED, ALTITUDE AND VERTICAL
AIRSPEED.
‘‘1. Appropriate STATIC SOURCE
selector—ALTERNATE. If switching the
STATIC SOURCE selector to ALTERNATE
does not correct the abnormal indications:
‘‘2. Rely on the flight instruments on the
opposite side and land as soon as
practicable.’’
Note 1: When a statement identical to that
in paragraph (f) of this AD has been included
in the general revisions of the applicable
flight manual, the general revisions may be
inserted into the flight manual, and the copy
of this AD may be removed from the flight
manual.
Modification of the Static System
(b) None.
PO 00000
Revision to Airplane Flight Manual
Fmt 4702
Sfmt 4702
(g) For airplanes having serial numbers 003
through 590 inclusive: Within 24 months
after the effective date of this AD, modify the
static system in accordance with Part A and
Part C of the Accomplishment Instructions of
Bombardier Service Bulletin 8–34–221,
Revision ‘A,’ dated September 15, 2003.
(h) For airplanes having serial numbers 591
through 598 inclusive: Within 24 months
after the effective date of this AD, modify the
static system in accordance with Part B and
Part C of the Accomplishment Instructions of
Bombardier Service Bulletin 8–34–221,
Revision ‘A,’ dated September 15, 2003.
Modifications Done According to Previous
Issue of Service Bulletin
(i) Modifications done before the effective
date of this AD in accordance with
Bombardier Service Bulletin 8–34–221, dated
May 27, 2003, are acceptable for compliance
with the applicable modifications specified
in paragraphs (g) and (h) of this AD.
E:\FR\FM\01FEP1.SGM
01FEP1
Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules
Alternative Methods of Compliance
(AMOCs)
(j) The Manager, New York Aircraft
Certification Office, 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.
Related Information
(k) Canadian airworthiness directive CF–
2003–25, dated October 10, 2003, also
addresses the subject of this AD.
Issued in Renton, Washington, on January
21, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–1808 Filed 1–31–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20220; Directorate
Identifier 2004–NM–152–AD]
RIN 2120–AA64
Airworthiness Directives; Aerospatiale
Model ATR42–200, –300, and –320
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Aerospatiale Model ATR42–200,
–300, and –320 series airplanes. This
proposed AD would require doing
repetitive inspections of the upper arms
of the MLG side braces for missing or
inadequately bonded identification
plates; replacing the upper arm if
necessary; and replacing the side brace
assembly with a modified part. This
proposed AD is prompted by an
operator who reported experiencing an
unlock warning for the MLG on the right
side of the airplane. We are proposing
this AD to prevent cracking of the upper
arms of the side braces of the MLG,
which could result in failure of the MLG
during landing and possible damage to
the airplane and injury to the flightcrew
and passengers.
DATES: We must receive comments on
this proposed AD by March 3, 2005.
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
SUMMARY:
VerDate jul<14>2003
14:57 Jan 31, 2005
Jkt 205001
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.
• By 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.
For service information identified in
this proposed AD, contact MessierDowty, BP 10, 78142 Velizy Cedex,
France.
You can examine the contents of this
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., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20220; the directorate identifier for this
docket is 2004–NM–152–AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1137;
fax (425) 227–1149.
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 under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20220; Directorate Identifier
2004–NM–152–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 submitted 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 our docket
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,
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
5081
business, labor union, etc.). You can
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can 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 DMS
receives them.
Discussion
´ ´
The Direction Generale de l’Aviation
Civile (DGAC), which is the
airworthiness authority for France,
notified us that an unsafe condition may
exist on certain Aerospatiale Model
ATR42–200, –300, and –320 series
airplanes. The DGAC advises that an
operator reported experiencing, during
taxiing, an unlock warning for the MLG
on the right side of the airplane.
Investigation found that the upper side
brace of the right MLG was cracked due
to accidental damage caused by the
location of certain identification plates
and possible corrosion introduced
during production. Cracking of the
upper arms of the side braces of the
MLG, if not corrected, could result in
failure of the MLG during landing and
possible damage to the airplane and
injury to the flightcrew and passengers.
Relevant Service Information
Messier-Dowty has issued Special
Inspection Service Bulletin 631–32–175,
dated January 7, 2004; and Service
Bulletin 631–32–176, Revision 1, dated
June 2, 2004. Special Inspection Service
Bulletin 631–32–175 describes
procedures for doing repetitive general
visual inspections of the upper arms of
the MLG side braces for missing or
inadequately bonded identification
plates having P/Ns D61565–1, D61566–
1, D61567–1, and D61568–1; and
replacing any upper arm having a
missing or inadequately-bonded
identification plate with a serviceable
upper arm having the same part
number. Service Bulletin 631–32–176
describes procedures for removing the
side brace assembly and replacing it
with a modified part. Modification of
the side brace assembly includes the
following actions:
E:\FR\FM\01FEP1.SGM
01FEP1
]]>Agencies
[Federal Register Volume 70, Number 20 (Tuesday, February 1, 2005)]
[Proposed Rules]
[Pages 5078-5081]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-1808]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20222; Directorate Identifier 2004-NM-230-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106,
-201, -202, -301, -311, and -315 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -
311, and -315 airplanes. The subject of this proposed AD is the pilot's
static system. This proposed AD would require
[[Page 5079]]
revising the airplane flight manual to include applicable procedures to
follow when the flightcrew receives abnormal indications of airspeed,
altitude, or vertical airspeed. This proposed AD would also require
modifying the static system. This proposed AD is prompted by a report
of a leak in the static pressure system, which could result in loss of
the static systems and consequent erroneous data displayed on the
pilot's flight instruments. We are proposing this AD to advise the
flightcrew of applicable procedures in the event of abnormal
indications of airspeed, altitude, or vertical airspeed; and to prevent
leaks in the static system, which could result in the loss of critical
flight information that could result in reduced controllability of the
airplane or controlled flight into terrain.
DATES: We must receive comments on this proposed AD by March 3, 2005.
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.
By 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.
For service information identified in this proposed AD, contact
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada.
You can examine the contents of this 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., room PL-
401, on the plaza level of the Nassif Building, Washington, DC. This
docket number is FAA-2005-20222; the directorate identifier for this
docket is 2004-NM-230-AD.
FOR FURTHER INFORMATION CONTACT: Ezra Sasson, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New
York 11590; telephone (516) 228-7320; 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 under ADDRESSES. Include ``Docket No. FAA-2005-20222;
Directorate Identifier 2004-NM-230-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 submitted 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 our
docket 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 can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
You can 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 DMS receives them.
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, notified the FAA that an unsafe condition may
exist on certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -
301, -311, and -315 airplanes. TCCA advises that an investigation of an
incident involving erroneous data displayed on the pilot's flight
instruments has revealed that a leak in the pilot's side static
pressure system, downstream of the alternate selector valve, could
result in the loss of both the pilot's normal and alternate static
systems. This condition, if not corrected, could result in the display
of abnormal indications of airspeed, altitude, or vertical airspeed due
to leaks in the static system and prolonged loss of critical flight
information that could result in reduced controllability of the
airplane or controlled flight into terrain.
Relevant Service Information
Bombardier has issued Service Bulletin 8-34-221, Revision `A,'
dated September 15, 2003. The service bulletin describes procedures to
modify the pilot's side static system to prevent leaks in the system.
For certain airplanes the modification provides increased independence
of the static pressure source for the pilot's primary and standby
flight instruments, and for certain other airplanes the modification
corrects the length of the static system hose.
TCCA mandated the service bulletin and issued Canadian
airworthiness directive CF-2003-25, dated October 10, 2003, to ensure
the continued airworthiness of these airplanes in Canada.
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, TCCA 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 products of this type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to provide procedures to the
flightcrew in the event of abnormal indications of airspeed, altitude,
or vertical airspeed; and to prevent leaks in the static system, which
could result in the loss of critical flight information that could
result in reduced controllability of the airplane or controlled flight
into terrain. This AD requires accomplishing the actions specified in
the service information described previously, except as discussed under
``Differences Between the Proposed AD and Canadian Airworthiness
Directive.''
Differences Between the Proposed AD and Canadian Airworthiness
Directive
This proposed AD advises revising the applicable de Havilland Dash
8 airplane flight manual to incorporate the text specified in paragraph
(f) of this
[[Page 5080]]
proposed AD. The Canadian AD does not include such a requirement. In
Canada, operators are mandated to use the latest flight manual and
therefore, TCCA is not required to issue an AD to require flight manual
revisions.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Revise AFM................................ 1 $65 None........................ $65 181 $11,765
Modify static system...................... 2 65 100-200..................... 230-330 181 41,630-59,730
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the United States Code. 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.
This rulemaking is promulgated 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
proposed AD.
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. 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 FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2005-
20222; Directorate Identifier 2004-NM-230-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by March 3, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-102, -103, -106, -
201, -202, -301, -311, and -315 airplanes, certificated in any
category; serial numbers 003 through 598 inclusive.
Unsafe Condition
(d) This AD was prompted by a report of a leak in the static
pressure system, which could result in loss of the static systems
and consequent erroneous data displayed on the pilot's flight
instruments. The subject of this AD is the pilot's static system. We
are issuing this AD to advise the flightcrew of applicable
procedures in the event of abnormal indications of airspeed,
altitude, or vertical airspeed; and to prevent leaks in the static
system, which could result in the loss of critical flight
information that could result in reduced controllability of the
airplane or controlled flight into terrain.
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.
Revision to Airplane Flight Manual
(f) Within 10 days after the effective date of this AD, revise
the Normal and Abnormal Procedures sections of the applicable de
Havilland Dash 8 flight manual to include the following statement in
paragraph 4.11.1 of 4.11 Pitot--Static and Stall Warning System
Failures. This may be done by inserting a copy of this AD in the
applicable flight manual.
``4.11.1 ABNORMAL INDICATIONS OF AIRSPEED, ALTITUDE AND VERTICAL
AIRSPEED.
``1. Appropriate STATIC SOURCE selector--ALTERNATE. If switching
the STATIC SOURCE selector to ALTERNATE does not correct the
abnormal indications:
``2. Rely on the flight instruments on the opposite side and
land as soon as practicable.''
Note 1: When a statement identical to that in paragraph (f) of
this AD has been included in the general revisions of the applicable
flight manual, the general revisions may be inserted into the flight
manual, and the copy of this AD may be removed from the flight
manual.
Modification of the Static System
(g) For airplanes having serial numbers 003 through 590
inclusive: Within 24 months after the effective date of this AD,
modify the static system in accordance with Part A and Part C of the
Accomplishment Instructions of Bombardier Service Bulletin 8-34-221,
Revision `A,' dated September 15, 2003.
(h) For airplanes having serial numbers 591 through 598
inclusive: Within 24 months after the effective date of this AD,
modify the static system in accordance with Part B and Part C of the
Accomplishment Instructions of Bombardier Service Bulletin 8-34-221,
Revision `A,' dated September 15, 2003.
Modifications Done According to Previous Issue of Service Bulletin
(i) Modifications done before the effective date of this AD in
accordance with Bombardier Service Bulletin 8-34-221, dated May 27,
2003, are acceptable for compliance with the applicable
modifications specified in paragraphs (g) and (h) of this AD.
[[Page 5081]]
Alternative Methods of Compliance (AMOCs)
(j) The Manager, New York Aircraft Certification Office,
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.
Related Information
(k) Canadian airworthiness directive CF-2003-25, dated October
10, 2003, also addresses the subject of this AD.
Issued in Renton, Washington, on January 21, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-1808 Filed 1-31-05; 8:45 am]
BILLING CODE 4910-13-P
