Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 Airplanes; Equipped with Certain Cockpit Door Installations, 18244-18247 [06-3435]
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18244
Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Proposed Rules
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.
Repetitive Inspections
(f) Before the airplane accumulates 28,000
total flight cycles, or within 18 months after
the effective date of this AD, whichever
occurs later: Do a high-frequency eddy
current inspection for cracking of the web of
the STA 2360 aft pressure bulkhead around
the fastener heads in the critical fastener
rows in the web lap joints, from the Y-chord
to the inner ring; in accordance with Part 2,
‘‘Access and Inspection,’’ of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2561, dated
September 22, 2005. Repeat the inspection
thereafter at intervals not to exceed 2,000
flight cycles until the modification in
paragraph (h) of this AD is done.
Repair
(g) If any cracking is found during any
inspection required by paragraph (f) of this
AD: Before further flight, do the applicable
action in paragraph (g)(1) or (g)(2) of this AD.
(1) If the cracking is within certain limits
specified in Boeing Alert Service Bulletin
747–53A2561, dated September 22, 2005,
(referencing the structural repair manual) do
the repair in accordance with the
Accomplishment Instructions of the alert
service bulletin.
(2) If the cracking is more than certain
limits specified in Boeing Alert Service
Bulletin 747–53A2561, dated September 22,
2005, or if the alert service bulletin specifies
to ask Boeing for repair data: Repair the
cracking using a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA. For a repair method to be
approved by the Manager, Seattle ACO, as
required by this paragraph, the Manager’s
approval letter must specifically refer to this
AD.
Modification
(h) Before the airplane accumulates 35,000
total flight cycles or within 18 months after
the effective date of this AD, whichever
occurs later: Modify the aft pressure
bulkhead using a method approved by the
Manager, Seattle ACO. For a repair method
to be approved by the Manager, Seattle ACO,
as required by this paragraph, the Manager’s
approval letter must specifically refer to this
AD. Doing this modification terminates the
repetitive inspection requirements of
paragraph (f) of this AD.
hsrobinson on PROD1PC70 with PROPOSALS
Alternative Methods of Compliance
(AMOCs)
(i)(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.
VerDate Aug<31>2005
15:25 Apr 10, 2006
Jkt 208001
Issued in Renton, Washington, on March
31, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–3433 Filed 4–10–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24411; Directorate
Identifier 2006–NM–033–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–102, –103, –106, –201,
–202, –301, –311, –314, and –315
Airplanes; Equipped with Certain
Cockpit Door Installations
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,
–314, and –315 airplanes. This proposed
AD would require modifying the hinge
attachment for the cockpit door from a
single-point attachment to a two-point
attachment. This proposed AD results
from a report that, during structural
testing of the cockpit door, the lower
hinge block rotated and caused the
mating hinge pin to disengage, and
caused excessive door deflection. We
are proposing this AD to prevent failure
of a door attachment, which could result
in uncontrolled release of the cockpit
door under certain fuselage
decompression conditions, and possible
damage to the airplane structure.
DATES: We must receive comments on
this proposed AD by May 11, 2006.
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.
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
• 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, New York Aircraft Certification
Office, FAA, 1600 Stewart Avenue, suite
410, Westbury, New York 11590;
telephone (516) 228–7325; 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 ‘‘FAA–2006–24411; Directorate
Identifier 2006–NM–033–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 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
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Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Proposed Rules
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–8–102, –103,
–106, –201, –202, –301, –311, –314, and
–315 airplanes. TCCA advises that,
during structural testing of the cockpit
door, the lower hinge block rotated and
caused the mating hinge pin to
disengage, and caused excessive door
deflection. The rotation of the lower
hinge block was caused by an
inadequate number of attachment bolts
for the hinge block. This condition, if
not corrected, could cause failure of a
door attachment, which could result in
uncontrolled release of the cockpit door
under certain fuselage decompression
18245
conditions, and possible damage to the
aircraft structure.
Relevant Service Information
Bombardier has issued the service
bulletins listed in the following table.
These service bulletins apply to
Bombardier Model DHC–8–102, –103,
–106, –201, –202, –301, –311, –314, and
–315 airplanes that have the serial
numbers specified in the table.
BOMBARDIER SERVICE BULLETINS
Use this Bombardier Service Bulletin—
For serial numbers—
8–52–54, Revision A, dated November 5, 2004 ......................................
003 through 451 inclusive, 453 through 463 inclusive, 465 through 489
inclusive, 491 through 505 inclusive, and 507.
452, 464, 490, 506, and 508 through 557 inclusive.
8–52–58, dated May 12, 2004 .................................................................
The service bulletins describe
procedures for modifying the cockpit
door from a single-point attachment to
a two-point attachment. The
modification involves the following
actions, as applicable, depending on the
configuration of the airplane: Reworking
the door fairing, reworking the door
post, installing a new strike plate,
installing a new hinge assembly,
aligning the hinges, and installing a new
label regarding alternate release of the
door. Accomplishing the actions
specified in the service information is
intended to adequately address the
unsafe condition.
For certain airplanes, the service
bulletins specify doing the
modifications listed in the following
table prior to or concurrently with the
procedures in the service bulletins.
PRIOR/CONCURRENT REQUIREMENTS
For airplanes affected by Bombardier Service Bulletin—
That have these serial numbers—
Do these modifications—
As specified in—
8–52–54, Revision A, dated November 5, 2004.
003 through 407 inclusive, 409
through 412 inclusive, and 414
through 433 inclusive.
Rework the cockpit door emergency release.
De Havilland Aircraft of Canada,
Limited, Modification 8/2337.
Install a new label regarding alternate release of the door.
Install the cockpit door .................
De Havilland Aircraft of Canada,
Limited, Modification 8/3339.
Bombardier Modsum 8Q200015.
Install the cockpit door .................
Install the cockpit door with a
blow-out door panel.
Bombardier Modsum 8Q420101.
Bombardier Modsum 8Q420143.
hsrobinson on PROD1PC70 with PROPOSALS
8–52–58, dated May 12, 2004 ......
452, 464, 490, 506, and 508
through 557 inclusive.
TCCA mandated the service
information and issued Canadian
airworthiness directive CF–3005–34,
dated August 29, 2005, to ensure the
continued airworthiness of these
airplanes in Canada.
Bombardier Service Bulletin 8–52–54
refers to Bombardier Modsum 8Q100859
as an additional source of service
information for installing a hinge pin
with a two-point attachment.
Bombardier Service Bulletin 8–52–58
refers to Bombardier Modsum 8Q900267
as an additional source of service
information for reworking and installing
the cockpit door, and reworking the
lower hinge attachment to provide a
downward-facing pin with a two-point
attachment.
VerDate Aug<31>2005
15:25 Apr 10, 2006
Jkt 208001
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 airplanes of this
type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD,
which would require accomplishing the
actions specified in the service
information described previously.
PO 00000
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Fmt 4702
Sfmt 4702
Costs of Compliance
This proposed AD would affect about
16 airplanes of U.S. registry. The
proposed actions would take between 3
and 6 work hours per airplane,
depending on the airplane
configuration. The average labor rate is
$80 per work hour. Required parts
would cost about $2,000 per airplane.
Based on these figures, the estimated
cost of the proposed AD for U.S.
operators is between $35,840 and
$39,680, or between $2,240 and $2,480
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
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Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Proposed Rules
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
the compliance times specified, unless the
actions have already been done.
1. The authority citation for part 39
continues to read as follows:
Modification
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
(f) Within 24 months after the effective
date of this AD, modify the cockpit door from
a single-point attachment to a two-point
attachment in accordance with the
Accomplishment Instructions of the
applicable service bulletin in Table 2 of this
AD.
TABLE 2.—BOMBARDIER SERVICE
BULLETINS
BOMBARDIER, INC. (FORMERLY DE HAVILLAND,
INC.): Docket No. FAA–2006–24411;
Directorate Identifier 2006–NM–033–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by May 11, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–102, –103, –106, –201, –202, –301,
–311, –314, and –315 airplanes, certificated
in any category; serial numbers 003 through
557 inclusive; equipped with cockpit door
installation part numbers (P/Ns) identified in
Table 1 of this AD.
TABLE 1.—COCKPIT DOOR
INSTALLATIONS AFFECTED BY THIS AD
P/N
Dash nos.
82510074 ..................
82510294 ..................
82510310 ..................
8Z4597 ......................
H85250010 ................
82510700 ..................
82510704 ..................
All.
All.
–001.
–001.
All.
All.
All except –502 and
–503.
Unsafe Condition
(d) This AD results from a report that,
during structural testing of the cockpit door,
the lower hinge block rotated and caused the
mating hinge pin to disengage, and caused
excessive door deflection. We are issuing this
AD to prevent failure of a door attachment,
which could result in uncontrolled release of
the cockpit door under certain fuselage
decompression conditions, and possible
damage to the aircraft structure.
Use this Bombardier
Service Bulletin—
8–52–54, Revision A,
dated November 5,
2004.
8–52–58, dated May
12, 2004.
For serial numbers—
003 through 451 inclusive, 453
through 463 inclusive, 465 through
489 inclusive, 491
through 505 inclusive, and 507.
452, 464, 490, 506,
and 508 through
557 inclusive.
Note 1: Bombardier Service Bulletin 8–52–
54 refers to Bombardier Modification
Summary (Modsum) 8Q100859 as an
additional source of service information for
installing a hinge pin with a two-point
attachment. Bombardier Service bulletin 8–
52–58 refers to Bombardier Modsum
8Q900267 as an additional source of service
information for reworking and installing the
cockpit door, and reworking the lower hinge
attachment to provide a downward-facing
pin with a two-point attachment.
Prior/Concurrent Requirements
(g) Prior to or concurrently with the
modification in paragraph (f) of this AD, do
the applicable actions specified in Table 3 of
this AD according to a method approved by
either the Manager, New York Aircraft
Certification (ACO), FAA; or Transport
Canada Civil Aviation (TCCA) (or its
delegated agent). One approved method is
the applicable modification or Modsum
listed in the ‘‘One approved method for
doing these actions’’ column of Table 3 of
this AD.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
TABLE 3.—BOMBARDIER SERVICE BULLETINS
hsrobinson on PROD1PC70 with PROPOSALS
For airplanes affected by Bombardier Service Bulletin—
That have these serial numbers—
Do these actions—
One approved method for doing
these actions—
8–52–54, Revision A, dated November 5, 2004.
003 through 407 inclusive, 409
through 412 inclusive, and 414
through 433 inclusive.
Rework the cockpit door emergency release.
De Havilland Aircraft of Canada,
Limited, Modification 8/2337.
Install a new label regarding alternate release of the door.
Install the cockpit door .................
De Havilland Aircraft of Canada,
Limited, Modification 8/3339.
Bombardier Modsum 8Q200015.
8–52–58, dated May 12, 2004 ......
VerDate Aug<31>2005
15:25 Apr 10, 2006
452, 464, 490, 506, and 508
through 557 inclusive.
Jkt 208001
PO 00000
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Fmt 4702
Sfmt 4702
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Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Proposed Rules
18247
TABLE 3.—BOMBARDIER SERVICE BULLETINS—Continued
For airplanes affected by Bombardier Service Bulletin—
That have these serial numbers—
One approved method for doing
these actions—
Do these actions—
Install the cockpit door .................
Install the cockpit door with a
blow-out door panel.
Actions Done in Accordance With Previous
Revision of Service Bulletin
(h) Actions done before the effective date
of this AD in accordance with Bombardier
Service Bulletin 8–52–54, dated May 12,
2004, are acceptable for compliance with the
corresponding requirements in paragraph (f)
of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(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
(j) Canadian airworthiness directive CF–
2005–34, dated August 29, 2005, also
addresses the subject of this AD.
Issued in Renton, Washington, on March
31, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–3435 Filed 4–10–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24366; Directorate
Identifier 2006–NM–040–AD]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135BJ
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
hsrobinson on PROD1PC70 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain EMBRAER Model EMB–135BJ
airplanes. This proposed AD would
require inspecting for missing fire
VerDate Aug<31>2005
15:25 Apr 10, 2006
Jkt 208001
blocking material on the left- and righthand partitions of the forward baggage
compartment door; replacing the seal on
both partitions; and performing
corrective action if necessary. This
proposed AD results from a report
indicating that certain airplanes were
delivered with the fire blocking material
missing and the seal improperly
installed on the partitions of the forward
baggage compartment door. We are
proposing this AD to detect and correct
such discrepancies on the partitions of
the forward baggage compartment door,
which, in the event of a fire in the
baggage compartment, could result in
smoke propagating into the main cabin.
DATES: We must receive comments on
this proposed AD by May 11, 2006.
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 Empresa Brasileira de
Aeronautica S.A. (EMBRAER), P.O. Box
343–CEP 12.225, Sao Jose dos Campos–
SP, Brazil, for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–2125; 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
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
Bombardier Modsum 8Q420101.
Bombardier Modsum 8Q420143.
comments to an address listed in the
section. Include the docket
number ‘‘FAA–2006–24366; Directorate
Identifier 2006–NM–040–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 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.
ADDRESSES
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
The Departmento de Aviacao Civil
(DAC), which is the airworthiness
authority for Brazil, notified us that an
unsafe condition may exist on certain
EMBRAER Model EMB–135BJ airplanes.
The DAC advises that certain airplanes
were delivered with the fire blocking
material missing and the seal
improperly installed on the left- and
right-hand partitions of the forward
baggage compartment door. These
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]]>Agencies
[Federal Register Volume 71, Number 69 (Tuesday, April 11, 2006)]
[Proposed Rules]
[Pages 18244-18247]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-3435]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24411; Directorate Identifier 2006-NM-033-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106,
-201, -202, -301, -311, -314, and -315 Airplanes; Equipped with Certain
Cockpit Door Installations
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, -314, and -315 airplanes. This proposed AD would require modifying
the hinge attachment for the cockpit door from a single-point
attachment to a two-point attachment. This proposed AD results from a
report that, during structural testing of the cockpit door, the lower
hinge block rotated and caused the mating hinge pin to disengage, and
caused excessive door deflection. We are proposing this AD to prevent
failure of a door attachment, which could result in uncontrolled
release of the cockpit door under certain fuselage decompression
conditions, and possible damage to the airplane structure.
DATES: We must receive comments on this proposed AD by May 11, 2006.
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: George Duckett, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, New York Aircraft
Certification Office, FAA, 1600 Stewart Avenue, suite 410, Westbury,
New York 11590; telephone (516) 228-7325; 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 ``FAA-2006-
24411; Directorate Identifier 2006-NM-033-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 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
[[Page 18245]]
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-8-102, -103, -106, -201, -202, -301, -311,
-314, and -315 airplanes. TCCA advises that, during structural testing
of the cockpit door, the lower hinge block rotated and caused the
mating hinge pin to disengage, and caused excessive door deflection.
The rotation of the lower hinge block was caused by an inadequate
number of attachment bolts for the hinge block. This condition, if not
corrected, could cause failure of a door attachment, which could result
in uncontrolled release of the cockpit door under certain fuselage
decompression conditions, and possible damage to the aircraft
structure.
Relevant Service Information
Bombardier has issued the service bulletins listed in the following
table. These service bulletins apply to Bombardier Model DHC-8-102, -
103, -106, -201, -202, -301, -311, -314, and -315 airplanes that have
the serial numbers specified in the table.
Bombardier Service Bulletins
------------------------------------------------------------------------
Use this Bombardier Service Bulletin-- For serial numbers--
------------------------------------------------------------------------
8-52-54, Revision A, dated November 5, 003 through 451 inclusive, 453
2004. through 463 inclusive, 465
through 489 inclusive, 491
through 505 inclusive, and
507.
8-52-58, dated May 12, 2004............ 452, 464, 490, 506, and 508
through 557 inclusive.
------------------------------------------------------------------------
The service bulletins describe procedures for modifying the cockpit
door from a single-point attachment to a two-point attachment. The
modification involves the following actions, as applicable, depending
on the configuration of the airplane: Reworking the door fairing,
reworking the door post, installing a new strike plate, installing a
new hinge assembly, aligning the hinges, and installing a new label
regarding alternate release of the door. Accomplishing the actions
specified in the service information is intended to adequately address
the unsafe condition.
For certain airplanes, the service bulletins specify doing the
modifications listed in the following table prior to or concurrently
with the procedures in the service bulletins.
Prior/Concurrent Requirements
----------------------------------------------------------------------------------------------------------------
For airplanes affected by Bombardier That have these serial Do these modifications--
Service Bulletin-- numbers-- As specified in--
----------------------------------------------------------------------------------------------------------------
8-52-54, Revision A, dated November 003 through 407 Rework the cockpit door De Havilland Aircraft
5, 2004. inclusive, 409 through emergency release. of Canada, Limited,
412 inclusive, and 414 Modification 8/2337.
through 433 inclusive.
Install a new label De Havilland Aircraft
regarding alternate of Canada, Limited,
release of the door. Modification 8/3339.
8-52-58, dated May 12, 2004.......... 452, 464, 490, 506, and Install the cockpit Bombardier Modsum
508 through 557 door. 8Q200015.
inclusive.
Install the cockpit Bombardier Modsum
door. 8Q420101.
Install the cockpit Bombardier Modsum
door with a blow-out 8Q420143.
door panel.
----------------------------------------------------------------------------------------------------------------
TCCA mandated the service information and issued Canadian
airworthiness directive CF-3005-34, dated August 29, 2005, to ensure
the continued airworthiness of these airplanes in Canada.
Bombardier Service Bulletin 8-52-54 refers to Bombardier Modsum
8Q100859 as an additional source of service information for installing
a hinge pin with a two-point attachment. Bombardier Service Bulletin 8-
52-58 refers to Bombardier Modsum 8Q900267 as an additional source of
service information for reworking and installing the cockpit door, and
reworking the lower hinge attachment to provide a downward-facing pin
with a two-point attachment.
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 airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously.
Costs of Compliance
This proposed AD would affect about 16 airplanes of U.S. registry.
The proposed actions would take between 3 and 6 work hours per
airplane, depending on the airplane configuration. The average labor
rate is $80 per work hour. Required parts would cost about $2,000 per
airplane. Based on these figures, the estimated cost of the proposed AD
for U.S. operators is between $35,840 and $39,680, or between $2,240
and $2,480 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
[[Page 18246]]
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
adding the following new airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2006-
24411; Directorate Identifier 2006-NM-033-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by May 11,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-102, -103, -106, -
201, -202, -301, -311, -314, and -315 airplanes, certificated in any
category; serial numbers 003 through 557 inclusive; equipped with
cockpit door installation part numbers (P/Ns) identified in Table 1
of this AD.
Table 1.--Cockpit Door Installations Affected by This AD
------------------------------------------------------------------------
P/N Dash nos.
------------------------------------------------------------------------
82510074.................................. All.
82510294.................................. All.
82510310.................................. -001.
8Z4597.................................... -001.
H85250010................................. All.
82510700.................................. All.
82510704.................................. All except -502 and -503.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from a report that, during structural
testing of the cockpit door, the lower hinge block rotated and
caused the mating hinge pin to disengage, and caused excessive door
deflection. We are issuing this AD to prevent failure of a door
attachment, which could result in uncontrolled release of the
cockpit door under certain fuselage decompression conditions, and
possible damage to the aircraft structure.
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.
Modification
(f) Within 24 months after the effective date of this AD, modify
the cockpit door from a single-point attachment to a two-point
attachment in accordance with the Accomplishment Instructions of the
applicable service bulletin in Table 2 of this AD.
Table 2.--Bombardier Service Bulletins
------------------------------------------------------------------------
Use this Bombardier Service Bulletin-- For serial numbers--
------------------------------------------------------------------------
8-52-54, Revision A, dated November 5, 003 through 451 inclusive,
2004. 453 through 463 inclusive,
465 through 489 inclusive,
491 through 505 inclusive,
and 507.
8-52-58, dated May 12, 2004............... 452, 464, 490, 506, and 508
through 557 inclusive.
------------------------------------------------------------------------
Note 1: Bombardier Service Bulletin 8-52-54 refers to Bombardier
Modification Summary (Modsum) 8Q100859 as an additional source of
service information for installing a hinge pin with a two-point
attachment. Bombardier Service bulletin 8-52-58 refers to Bombardier
Modsum 8Q900267 as an additional source of service information for
reworking and installing the cockpit door, and reworking the lower
hinge attachment to provide a downward-facing pin with a two-point
attachment.
Prior/Concurrent Requirements
(g) Prior to or concurrently with the modification in paragraph
(f) of this AD, do the applicable actions specified in Table 3 of
this AD according to a method approved by either the Manager, New
York Aircraft Certification (ACO), FAA; or Transport Canada Civil
Aviation (TCCA) (or its delegated agent). One approved method is the
applicable modification or Modsum listed in the ``One approved
method for doing these actions'' column of Table 3 of this AD.
Table 3.--Bombardier Service Bulletins
----------------------------------------------------------------------------------------------------------------
For airplanes affected by Bombardier That have these serial One approved method for
Service Bulletin-- numbers-- Do these actions-- doing these actions--
----------------------------------------------------------------------------------------------------------------
8-52-54, Revision A, dated November 003 through 407 Rework the cockpit door De Havilland Aircraft
5, 2004. inclusive, 409 through emergency release. of Canada, Limited,
412 inclusive, and 414 Modification 8/2337.
through 433 inclusive.
Install a new label De Havilland Aircraft
regarding alternate of Canada, Limited,
release of the door. Modification 8/3339.
8-52-58, dated May 12, 2004.......... 452, 464, 490, 506, and Install the cockpit Bombardier Modsum
508 through 557 door. 8Q200015.
inclusive.
[[Page 18247]]
Install the cockpit Bombardier Modsum
door. 8Q420101.
Install the cockpit Bombardier Modsum
door with a blow-out 8Q420143.
door panel.
----------------------------------------------------------------------------------------------------------------
Actions Done in Accordance With Previous Revision of Service Bulletin
(h) Actions done before the effective date of this AD in
accordance with Bombardier Service Bulletin 8-52-54, dated May 12,
2004, are acceptable for compliance with the corresponding
requirements in paragraph (f) of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(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
(j) Canadian airworthiness directive CF-2005-34, dated August
29, 2005, also addresses the subject of this AD.
Issued in Renton, Washington, on March 31, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-3435 Filed 4-10-06; 8:45 am]
BILLING CODE 4910-13-P
