Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 8187-8190 [E8-2747]
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Federal Register / Vol. 73, No. 30 / Wednesday, February 13, 2008 / Rules and Regulations
‘‘Before opening doors:
• IF DEPRESS VALVE selected in MAN mode:
—DEPRESS VALVE MAN CLT .................................................................................................................
—DP (Diff press) .........................................................................................................................................
• If evacuation required:
—Evacuation ..............................................................................................................................................
—BAT (before leaving A/C) ......................................................................................................................
• If evacuation not required:
—CABIN CREW and PASSENGERS .........................................................................................................
Note 1: When the information described in
paragraphs (f)(1), (f)(2), or (f)(3) has been
included in the general revisions of the AFM,
the general revisions may be inserted in the
applicable AFM, and the copy of the AD may
be removed from that AFM.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
[Docket No. FAA–2008–0167; Directorate
Identifier 2008–NM–029–AD; Amendment
39–15374; AD 2008–04–02]
RIN 2120–AA64
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tom Stafford,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1622; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) Airworthiness
Directive 2007–0093 R1, dated April 17,
2007, for related information.
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Material Incorporated by Reference
(i) None.
Issued in Renton, Washington, on February
4, 2008.
Kevin Hull,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–2587 Filed 2–12–08; 8:45 am]
BILLING CODE 4910–13–P
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Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier Model DHC–8–400 series
airplanes. This AD requires inspecting
all barrel nuts to determine if the barrel
nuts have a certain marking, inspecting
affected bolts to determine if the bolts
are pre-loaded correctly, and replacing
all hardware if the pre-load is incorrect.
For airplanes on which the pre-load is
correct, this AD requires doing
repetitive visual inspections for
cracking of the barrel nuts and cradles
and replacing all hardware for all
cracked barrel nuts. This AD also
requires replacement of all hardware for
certain affected barrel nuts that do not
have cracking, which would end the
repetitive inspections for those
airplanes. This AD also provides an
optional replacement for all affected
barrel nuts. This AD results from reports
of cracking in the barrel nuts at the four
primary front spar wing-to-fuselage
attachment joints. We are issuing this
AD to detect and correct cracking of the
barrel nuts at the wing front spar wingto-fuselage joints, which could result in
reduced structural integrity of the wingto-fuselage attachments and consequent
detachment of the wing.
DATES: This AD becomes effective
February 13, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of February 13, 2008.
We must receive comments on this
AD by March 14, 2008.
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8187
Full Open.
Check zero.
Initiate.
OFF/R.
Notify’’.
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building, Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building, Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Bombardier, Inc.,
Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview,
Ontario M3K 1Y5, Canada.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Pong Lee, 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) 228–7324; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
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
scheduled maintenance, an operator
found cracks in the barrel nut at one of
the four primary front spar wing-tofuselage attachment joints. Investigation
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determined that the cracks were due to
hydrogen embrittlement and that the
problem is likely restricted to a batch of
166 barrel nuts from one supplier. In
addition, another operator has reported
finding cracked barrel nuts at three of
the four wing front spar wing-tofuselage joints on one aircraft. All three
barrel nuts were from the suspect batch.
Cracking of the barrel nuts, if not
detected and corrected, could result in
reduced structural integrity of the wingto-fuselage attachments and consequent
detachment of the wing.
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Relevant Service Information
Bombardier has issued Alert Service
Bulletin A84–57–19, Revision A, dated
February 6, 2008. The service bulletin
describes the following procedures:
• Determining whether the inboard
and outboard bolts are correctly preloaded.
• Replacing all hardware at locations
where the pre-load is incorrect.
• Doing a visual inspection of the
barrel nut and cradle for cracking.
• Replacing cracked barrel nuts with
all new hardware.
• Doing an inspection for certain
markings of the barrel nuts.
• Replacing barrel nuts having the
affected markings.
TCCA mandated the service bulletin
and issued Canadian emergency
airworthiness directive CF–2008–11,
dated February 5, 2008, to ensure the
continued airworthiness of these
airplanes in Canada.
FAA’s Determination and Requirements
of This AD
These airplanes 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
detect and correct cracking of the barrel
nuts at the wing front spar wing-tofuselage joints, which could result in
reduced structural integrity of the wingto-fuselage attachments and consequent
detachment of the wing.
This AD requires the following
actions:
• Inspecting all barrel nuts to
determine if the barrel nuts have a
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16:56 Feb 12, 2008
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marking of LH7940T SPS 01 (all barrel
nuts with this marking will also have a
yellow dot identifier).
• Inspecting (repetitively) affected
bolts to determine if the bolts are preloaded correctly.
• Replacing all hardware if the preload is incorrect.
• Doing repetitive visual inspections
for cracking of the barrel nuts and
cradles for airplanes on which the preload is correct.
• Replacing all hardware for all
cracked barrel nuts.
• Replacing all hardware for certain
affected barrel nuts that do not have
cracking, which would end the
repetitive inspections for those
airplanes. This AD also provides an
optional replacement for all affected
barrel nuts.
Differences Between the AD and
Canadian Emergency Airworthiness
Directive
The Canadian emergency
airworthiness directive recommends
accomplishing the inspection of the
barrel nuts within 100 flight hours. We
have determined, however, that the
inspection must be done within 50
flight hours to adequately address the
unsafe condition. In developing an
appropriate compliance time for all
airplanes that are affected by this AD,
we considered not only the
manufacturer’s recommendation, but
the degree of urgency associated with
addressing the subject unsafe condition,
the average utilization of the affected
fleet, and the time necessary to perform
the required inspections. We have
coordinated this difference with TCCA.
We consider this AD interim action.
We are currently considering requiring
the replacement of all hardware for all
barrel nuts identified with a marking of
LH7940T SPS 01, as required by the
Canadian emergency airworthiness
directive. However, the planned
compliance time for the replacement
would allow enough time to provide
notice and opportunity for prior public
comment on the merits of the
modification. In order to ensure
continued operational safety in the
interim, this AD requires repetitive
inspections for cracking of the suspect
barrel nuts every 100 flight hours until
the replacement is done.
FAA’s Justification and Determination
of the Effective Date
Cracking of the barrel nuts at the wing
front spar wing-to-fuselage joints could
result in reduced structural integrity of
the wing-to-fuselage attachments and
consequent detachment of the wing.
Because of our requirement to promote
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safe flight of civil aircraft and thus, the
critical need to assure the structural
integrity of the front spar wing-tofuselage attachment joints and the short
compliance time involved with this
action, this AD must be issued
immediately.
Because an unsafe condition exists
that requires the immediate adoption of
this AD, we find that notice and
opportunity for prior public comment
hereon are impracticable and that good
cause exists for making this amendment
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2008–0167; Directorate Identifier 2008–
NM–029–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
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.
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Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the 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 AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2008–04–02 BOMBARDIER, INC. (FORMERLY DE
HAVILLAND, INC.): Amendment 39–15374.
Docket No. FAA–2008–0167; Directorate
Identifier 2008–NM–029–AD.
Effective Date
(a) This AD becomes effective February 13,
2008.
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Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–400, DHC–8–401, and DHC–8–402
airplanes, certificated in any category; serial
numbers 4001 and 4003 through 4176
inclusive.
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16:56 Feb 12, 2008
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Unsafe Condition
(d) This AD results from reports of cracking
in the barrel nuts at the four primary front
spar wing-to-fuselage attachment joints. We
are issuing this AD to detect and correct
cracking of the barrel nuts at the wing front
spar wing-to-fuselage joints, which could
result in reduced structural integrity of the
wing-to-fuselage attachments and consequent
detachment of the wing.
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.
Inspections and Corrective Actions
(f) Within 50 flight hours after the effective
date of this AD, inspect all barrel nuts, part
number DSC228–16, to determine if the
barrel nuts are identified with a marking of
LH7940T SPS 01. Inspect in accordance with
the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84–57–
19, Revision A, dated February 6, 2008.
(1) If no barrel nuts are identified with a
marking of LH7940T SPS 01, no further
actions are required by this paragraph.
(2) If any barrel nut is found that is
identified with a marking of LH7940T SPS
01, before further flight, inspect the inboard
and outboard bolts to determine if the bolts
are pre-loaded correctly. Inspect in
accordance with the Accomplishment
Instructions of Bombardier Alert Service
Bulletin A84–57–19, Revision A, dated
February 6, 2008.
(i) If the pre-load is incorrect (i.e., the ring
can be rotated), before further flight, replace
all hardware at that location in accordance
with the Accomplishment Instructions of the
alert service bulletin.
(ii) If the preload is correct, before further
flight, do a visual inspection for cracking of
the barrel nuts and cradles in accordance
with the Accomplishment Instructions of the
alert service bulletin.
(A) If no cracking of the barrel nut and
cradle is found, do the applicable action
required by paragraph (g) of this AD.
(B) If no cracking of the barrel nut is found
and only cracking of the cradle is found, no
action is required by this paragraph provided
that the applicable corrective action specified
in paragraph (g) of this AD is done.
(C) If any cracking of the barrel nut is
found, before next flight, replace all
hardware only at that location in accordance
with the Accomplishment Instructions of the
alert service bulletin.
(g) For any barrel nuts on which no
cracking of the barrel nut was found during
the inspection required by paragraph (f)(2)(ii)
of this AD, do the applicable corrective
action specified in paragraph (g)(1), (g)(2),
(g)(3), (g)(4), or (g)(5) of this AD at the
compliance time specified in the applicable
paragraph.
(1) If four barrel nuts having no cracking
are found, do the actions specified in
paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of
this AD.
(i) Within 50 flight hours after doing the
inspection required by paragraph (f)(2)(ii) of
this AD, repeat the inspection specified in
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8189
paragraph (f)(2) of this AD. Thereafter, repeat
the inspection at intervals not to exceed 50
flight hours until the replacement specified
in paragraph (g)(1)(ii) of this AD is done.
(ii) Within 100 flight hours after doing the
inspection required by paragraph (f)(2)(ii) of
this AD, replace all hardware at the left-hand
outboard location and the right-hand
outboard location in accordance with the
Accomplishment Instructions of Bombardier
Alert Service Bulletin A84–57–19, Revision
A, dated February 6, 2008. Replacing the
barrel nuts on the outboard locations
terminates the requirement to do the
repetitive inspections specified in paragraph
(g)(1)(i) of this AD.
(iii) Within 100 flight hours after doing the
replacement required by paragraph (g)(1)(ii)
of this AD, repeat the inspection specified in
paragraph (f)(2) of this AD for the remaining
barrel nuts identified with a marking of
LH7940T SPS 01. Thereafter, repeat the
inspection at intervals not to exceed 100
flight hours until the replacement of all
hardware at those locations is done. Do the
inspection and replacement in accordance
with the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84–57–
19, Revision A, dated February 6, 2008.
(2) If three barrel nuts having no cracking
are found, do the actions specified in
paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of
this AD.
(i) Within 50 flight hours after doing the
inspection required by paragraph (f)(2)(ii) of
this AD, repeat the inspection specified in
paragraph (f)(2) of this AD. Thereafter, repeat
the inspection at intervals not to exceed 50
flight hours until the replacement specified
in paragraph (g)(2)(ii) of this AD is done.
(ii) Within 100 flight hours after doing the
inspection required by paragraph (f)(2)(ii) of
this AD, replace all hardware for one affected
barrel nut at the outboard location, on the
side with two affected barrel nuts, in
accordance with the Accomplishment
Instructions of Bombardier Alert Service
Bulletin A84–57–19, Revision A, dated
February 6, 2008. Replacing the barrel nut on
the outboard location terminates the
requirement to do the repetitive inspections
specified in paragraph (g)(2)(i) of this AD.
(iii) Within 100 flight hours after doing the
replacement required by paragraph (g)(2)(ii)
of this AD, repeat the inspection specified in
paragraph (f)(2) of this AD for the remaining
barrel nuts identified with a marking of
LH7940T SPS 01. Thereafter, repeat the
inspection at intervals not to exceed 100
flight hours until the replacement of all
hardware at those locations is done. Do the
inspection and replacement in accordance
with the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84–57–
19, Revision A, dated February 6, 2008.
(3) If two barrel nuts having no cracking
are found and both nuts are on the same side,
do the actions specified in paragraphs
(g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of this AD.
(i) Within 100 flight hours after doing the
inspection required by paragraph (f)(2)(ii) of
this AD, repeat the inspection specified in
paragraph (f)(2) of this AD. Thereafter, repeat
the inspection at intervals not to exceed 100
flight hours until the replacement specified
in paragraph (g)(3)(ii) of this AD is done.
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(ii) Within 500 flight hours after doing the
inspection required by paragraph (f)(2)(ii) of
this AD, replace all hardware for one affected
barrel nut at the outboard location that has
two affected barrel nuts in accordance with
the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84–57–
19, Revision A, dated February 6, 2008.
Replacing the barrel nut on the outboard
location terminates the requirement to do the
repetitive inspections specified in paragraph
(g)(3)(i) of this AD.
(iii) Within 100 flight hours after doing the
replacement required by paragraph (g)(3)(ii)
of this AD, repeat the inspection specified in
paragraph (f)(2) of this AD for the remaining
barrel nut identified with a marking of
LH7940T SPS 01. Thereafter, repeat the
inspection at intervals not to exceed 100
flight hours until the replacement of all
hardware at that location is done. Do the
inspection and replacement in accordance
with the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84–57–
19, Revision A, dated February 6, 2008.
(4) If two barrel nuts having no cracking
are found and are on opposite sides, within
100 flight hours after doing the inspection
required by paragraph (f)(2)(ii) of this AD,
repeat the inspection specified in paragraph
(f)(2) of this AD. Thereafter, repeat the
inspection at intervals not to exceed 100
flight hours until the replacement of all
hardware at those locations is done. Do the
inspection and replacement in accordance
with the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84–57–
19, Revision A, dated February 6, 2008.
(5) If one barrel nut having no cracking is
found, within 100 flight hours after doing the
inspection required by paragraph (f)(2)(ii) of
this AD, repeat the inspection specified in
paragraph (f)(2) of this AD. Thereafter, repeat
the inspection at intervals not to exceed 100
flight hours until the replacement of all
hardware at that location is done. Do the
inspection and replacement in accordance
with the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84–57–
19, Revision A, dated February 6, 2008.
Optional Replacement
(h) Replacement of all hardware for all
barrel nuts, part number DSC228–16,
identified with a marking of LH7940T SPS
01, constitutes terminating action for this AD.
Replacement must be done in accordance
with the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84–57–
19, Revision A, dated February 6, 2008.
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Actions Accomplished According to
Previous Issue of Alert Service Bulletin
(i) Actions accomplished before the
effective date of this AD in accordance with
Bombardier Alert Service Bulletin A84–57–
19, dated February 1, 2008, are acceptable for
compliance with the corresponding actions
specified in this AD.
Actions Accomplished According to
Bombardier Alert Service Bulletin A84–57–
18
(j) For airplanes on which the actions
specified in Bombardier Alert Service
Bulletin A84–57–18, dated January 16, 2008,
were accomplished before the effective date
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Jkt 214001
of this AD and on which no barrel nuts were
found that were identified with a marking of
LH7940T SPS 01: No further action is
required by this AD.
Parts Installation
(k) As of the effective date of this AD, no
person may install a barrel nut, part number
DSC228–16, identified with a marking of
LH7940T SPS 01, on any airplane.
Special Flight Permit
(l) Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), may be issued to operate the
airplane to a location where the requirements
of this AD can be accomplished but
concurrence by the Manager, New York
Aircraft Certification Office, FAA, is required
prior to issuance of the special flight permit.
Before using any approved special flight
permits, notify your appropriate principal
inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your
local FSDO. Special flight permits may be
permitted provided that the conditions
specified in paragraph (l)(1), (l)(2), (l)(3),
(l)(4), and (l)(5) of this AD are met.
(1) Both the right-hand side and left-hand
side of the airplane must have at least one
barrel nut that is not within the suspect batch
(i.e., barrel nut is not identified with a
marking of LH7940T SPS 01). The barrel nuts
that are not within the suspect batch must be
in good working condition (i.e., no cracking
of the barrel nut).
(2) No passengers and no cargo are
onboard.
(3) Airplane must operate in fair weather
conditions with a low risk of turbulence.
(4) Airplane must operate with reduced
airspeed. For further information, contact
Bombardier, Q Series 24 Hour Service
Customer Response Center, at: Tel: 1–416–
375–4000; Fax: 1–416–375–4539; E-mail:
thd.qseries@aero.bombardier.com.
(5) All of the conditions specified in
paragraphs (l)(1), (l)(2), (l)(3), and (l)(4) of
this AD are on a case-by-case basis. Contact
your appropriate principal inspector (PI) in
the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO, for
assistance.
Alternative Methods of Compliance
(AMOCs)
(m)(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) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(n) Canadian emergency airworthiness
directive CF–2008–11, dated February 5,
2008.
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Material Incorporated by Reference
(o) You must use Bombardier Alert Service
Bulletin A84–57–19, Revision A, dated
February 6, 2008, to perform the actions that
are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register approved the incorporation
by reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5,
Canada, for a copy of this service
information. You may review copies at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at
the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on February
7, 2008.
Kevin Hull,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–2747 Filed 2–12–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF ENERGY
Federal Energy Regulatory
Commission
18 CFR Part 157
[Docket No. RM81–19–000]
Natural Gas Pipelines; Project Cost
and Annual Limits
February 5, 2008.
Federal Energy Regulatory
Commission, DOE.
AGENCY:
ACTION:
Final rule.
SUMMARY: Pursuant to the authority
delegated by 18 CFR 375.308(x)(1), the
Director of the Office of Energy Projects
(OEP) computes and publishes the
project cost and annual limits for
natural gas pipelines blanket
construction certificates for each
calendar year.
This final rule is effective
February 13, 2008 and establishes cost
limits applicable from January 1, 2008
through December 31, 2008.
DATES:
FOR FURTHER INFORMATION CONTACT:
Michael J. McGehee, Chief, Certificates
Branch 1, Division of Pipeline
Certificates, (202) 502–8962.
E:\FR\FM\13FER1.SGM
13FER1
]]>Agencies
[Federal Register Volume 73, Number 30 (Wednesday, February 13, 2008)]
[Rules and Regulations]
[Pages 8187-8190]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-2747]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0167; Directorate Identifier 2008-NM-029-AD;
Amendment 39-15374; AD 2008-04-02]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier Model DHC-8-400 series airplanes. This AD requires
inspecting all barrel nuts to determine if the barrel nuts have a
certain marking, inspecting affected bolts to determine if the bolts
are pre-loaded correctly, and replacing all hardware if the pre-load is
incorrect. For airplanes on which the pre-load is correct, this AD
requires doing repetitive visual inspections for cracking of the barrel
nuts and cradles and replacing all hardware for all cracked barrel
nuts. This AD also requires replacement of all hardware for certain
affected barrel nuts that do not have cracking, which would end the
repetitive inspections for those airplanes. This AD also provides an
optional replacement for all affected barrel nuts. This AD results from
reports of cracking in the barrel nuts at the four primary front spar
wing-to-fuselage attachment joints. We are issuing this AD to detect
and correct cracking of the barrel nuts at the wing front spar wing-to-
fuselage joints, which could result in reduced structural integrity of
the wing-to-fuselage attachments and consequent detachment of the wing.
DATES: This AD becomes effective February 13, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of February 13,
2008.
We must receive comments on this AD by March 14, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building, Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building, Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Bombardier,
Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Pong Lee, 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) 228-7324; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
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 scheduled maintenance, an operator found cracks in the barrel
nut at one of the four primary front spar wing-to-fuselage attachment
joints. Investigation
[[Page 8188]]
determined that the cracks were due to hydrogen embrittlement and that
the problem is likely restricted to a batch of 166 barrel nuts from one
supplier. In addition, another operator has reported finding cracked
barrel nuts at three of the four wing front spar wing-to-fuselage
joints on one aircraft. All three barrel nuts were from the suspect
batch. Cracking of the barrel nuts, if not detected and corrected,
could result in reduced structural integrity of the wing-to-fuselage
attachments and consequent detachment of the wing.
Relevant Service Information
Bombardier has issued Alert Service Bulletin A84-57-19, Revision A,
dated February 6, 2008. The service bulletin describes the following
procedures:
Determining whether the inboard and outboard bolts are
correctly pre-loaded.
Replacing all hardware at locations where the pre-load is
incorrect.
Doing a visual inspection of the barrel nut and cradle for
cracking.
Replacing cracked barrel nuts with all new hardware.
Doing an inspection for certain markings of the barrel
nuts.
Replacing barrel nuts having the affected markings.
TCCA mandated the service bulletin and issued Canadian emergency
airworthiness directive CF-2008-11, dated February 5, 2008, to ensure
the continued airworthiness of these airplanes in Canada.
FAA's Determination and Requirements of This AD
These airplanes 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 detect and correct cracking of
the barrel nuts at the wing front spar wing-to-fuselage joints, which
could result in reduced structural integrity of the wing-to-fuselage
attachments and consequent detachment of the wing.
This AD requires the following actions:
Inspecting all barrel nuts to determine if the barrel nuts
have a marking of LH7940T SPS 01 (all barrel nuts with this marking
will also have a yellow dot identifier).
Inspecting (repetitively) affected bolts to determine if
the bolts are pre-loaded correctly.
Replacing all hardware if the pre-load is incorrect.
Doing repetitive visual inspections for cracking of the
barrel nuts and cradles for airplanes on which the pre-load is correct.
Replacing all hardware for all cracked barrel nuts.
Replacing all hardware for certain affected barrel nuts
that do not have cracking, which would end the repetitive inspections
for those airplanes. This AD also provides an optional replacement for
all affected barrel nuts.
Differences Between the AD and Canadian Emergency Airworthiness
Directive
The Canadian emergency airworthiness directive recommends
accomplishing the inspection of the barrel nuts within 100 flight
hours. We have determined, however, that the inspection must be done
within 50 flight hours to adequately address the unsafe condition. In
developing an appropriate compliance time for all airplanes that are
affected by this AD, we considered not only the manufacturer's
recommendation, but the degree of urgency associated with addressing
the subject unsafe condition, the average utilization of the affected
fleet, and the time necessary to perform the required inspections. We
have coordinated this difference with TCCA.
We consider this AD interim action. We are currently considering
requiring the replacement of all hardware for all barrel nuts
identified with a marking of LH7940T SPS 01, as required by the
Canadian emergency airworthiness directive. However, the planned
compliance time for the replacement would allow enough time to provide
notice and opportunity for prior public comment on the merits of the
modification. In order to ensure continued operational safety in the
interim, this AD requires repetitive inspections for cracking of the
suspect barrel nuts every 100 flight hours until the replacement is
done.
FAA's Justification and Determination of the Effective Date
Cracking of the barrel nuts at the wing front spar wing-to-fuselage
joints could result in reduced structural integrity of the wing-to-
fuselage attachments and consequent detachment of the wing. Because of
our requirement to promote safe flight of civil aircraft and thus, the
critical need to assure the structural integrity of the front spar
wing-to-fuselage attachment joints and the short compliance time
involved with this action, this AD must be issued immediately.
Because an unsafe condition exists that requires the immediate
adoption of this AD, we find that notice and opportunity for prior
public comment hereon are impracticable and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2008-0167; Directorate Identifier 2008-NM-029-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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.
[[Page 8189]]
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the 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 AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2008-04-02 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-15374. Docket No. FAA-2008-0167; Directorate Identifier 2008-NM-
029-AD.
Effective Date
(a) This AD becomes effective February 13, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400, DHC-8-401,
and DHC-8-402 airplanes, certificated in any category; serial
numbers 4001 and 4003 through 4176 inclusive.
Unsafe Condition
(d) This AD results from reports of cracking in the barrel nuts
at the four primary front spar wing-to-fuselage attachment joints.
We are issuing this AD to detect and correct cracking of the barrel
nuts at the wing front spar wing-to-fuselage joints, which could
result in reduced structural integrity of the wing-to-fuselage
attachments and consequent detachment of the wing.
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.
Inspections and Corrective Actions
(f) Within 50 flight hours after the effective date of this AD,
inspect all barrel nuts, part number DSC228-16, to determine if the
barrel nuts are identified with a marking of LH7940T SPS 01. Inspect
in accordance with the Accomplishment Instructions of Bombardier
Alert Service Bulletin A84-57-19, Revision A, dated February 6,
2008.
(1) If no barrel nuts are identified with a marking of LH7940T
SPS 01, no further actions are required by this paragraph.
(2) If any barrel nut is found that is identified with a marking
of LH7940T SPS 01, before further flight, inspect the inboard and
outboard bolts to determine if the bolts are pre-loaded correctly.
Inspect in accordance with the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84-57-19, Revision A, dated
February 6, 2008.
(i) If the pre-load is incorrect (i.e., the ring can be
rotated), before further flight, replace all hardware at that
location in accordance with the Accomplishment Instructions of the
alert service bulletin.
(ii) If the preload is correct, before further flight, do a
visual inspection for cracking of the barrel nuts and cradles in
accordance with the Accomplishment Instructions of the alert service
bulletin.
(A) If no cracking of the barrel nut and cradle is found, do the
applicable action required by paragraph (g) of this AD.
(B) If no cracking of the barrel nut is found and only cracking
of the cradle is found, no action is required by this paragraph
provided that the applicable corrective action specified in
paragraph (g) of this AD is done.
(C) If any cracking of the barrel nut is found, before next
flight, replace all hardware only at that location in accordance
with the Accomplishment Instructions of the alert service bulletin.
(g) For any barrel nuts on which no cracking of the barrel nut
was found during the inspection required by paragraph (f)(2)(ii) of
this AD, do the applicable corrective action specified in paragraph
(g)(1), (g)(2), (g)(3), (g)(4), or (g)(5) of this AD at the
compliance time specified in the applicable paragraph.
(1) If four barrel nuts having no cracking are found, do the
actions specified in paragraphs (g)(1)(i), (g)(1)(ii), and
(g)(1)(iii) of this AD.
(i) Within 50 flight hours after doing the inspection required
by paragraph (f)(2)(ii) of this AD, repeat the inspection specified
in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at
intervals not to exceed 50 flight hours until the replacement
specified in paragraph (g)(1)(ii) of this AD is done.
(ii) Within 100 flight hours after doing the inspection required
by paragraph (f)(2)(ii) of this AD, replace all hardware at the
left-hand outboard location and the right-hand outboard location in
accordance with the Accomplishment Instructions of Bombardier Alert
Service Bulletin A84-57-19, Revision A, dated February 6, 2008.
Replacing the barrel nuts on the outboard locations terminates the
requirement to do the repetitive inspections specified in paragraph
(g)(1)(i) of this AD.
(iii) Within 100 flight hours after doing the replacement
required by paragraph (g)(1)(ii) of this AD, repeat the inspection
specified in paragraph (f)(2) of this AD for the remaining barrel
nuts identified with a marking of LH7940T SPS 01. Thereafter, repeat
the inspection at intervals not to exceed 100 flight hours until the
replacement of all hardware at those locations is done. Do the
inspection and replacement in accordance with the Accomplishment
Instructions of Bombardier Alert Service Bulletin A84-57-19,
Revision A, dated February 6, 2008.
(2) If three barrel nuts having no cracking are found, do the
actions specified in paragraphs (g)(2)(i), (g)(2)(ii), and
(g)(2)(iii) of this AD.
(i) Within 50 flight hours after doing the inspection required
by paragraph (f)(2)(ii) of this AD, repeat the inspection specified
in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at
intervals not to exceed 50 flight hours until the replacement
specified in paragraph (g)(2)(ii) of this AD is done.
(ii) Within 100 flight hours after doing the inspection required
by paragraph (f)(2)(ii) of this AD, replace all hardware for one
affected barrel nut at the outboard location, on the side with two
affected barrel nuts, in accordance with the Accomplishment
Instructions of Bombardier Alert Service Bulletin A84-57-19,
Revision A, dated February 6, 2008. Replacing the barrel nut on the
outboard location terminates the requirement to do the repetitive
inspections specified in paragraph (g)(2)(i) of this AD.
(iii) Within 100 flight hours after doing the replacement
required by paragraph (g)(2)(ii) of this AD, repeat the inspection
specified in paragraph (f)(2) of this AD for the remaining barrel
nuts identified with a marking of LH7940T SPS 01. Thereafter, repeat
the inspection at intervals not to exceed 100 flight hours until the
replacement of all hardware at those locations is done. Do the
inspection and replacement in accordance with the Accomplishment
Instructions of Bombardier Alert Service Bulletin A84-57-19,
Revision A, dated February 6, 2008.
(3) If two barrel nuts having no cracking are found and both
nuts are on the same side, do the actions specified in paragraphs
(g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of this AD.
(i) Within 100 flight hours after doing the inspection required
by paragraph (f)(2)(ii) of this AD, repeat the inspection specified
in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at
intervals not to exceed 100 flight hours until the replacement
specified in paragraph (g)(3)(ii) of this AD is done.
[[Page 8190]]
(ii) Within 500 flight hours after doing the inspection required
by paragraph (f)(2)(ii) of this AD, replace all hardware for one
affected barrel nut at the outboard location that has two affected
barrel nuts in accordance with the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84-57-19, Revision A, dated
February 6, 2008. Replacing the barrel nut on the outboard location
terminates the requirement to do the repetitive inspections
specified in paragraph (g)(3)(i) of this AD.
(iii) Within 100 flight hours after doing the replacement
required by paragraph (g)(3)(ii) of this AD, repeat the inspection
specified in paragraph (f)(2) of this AD for the remaining barrel
nut identified with a marking of LH7940T SPS 01. Thereafter, repeat
the inspection at intervals not to exceed 100 flight hours until the
replacement of all hardware at that location is done. Do the
inspection and replacement in accordance with the Accomplishment
Instructions of Bombardier Alert Service Bulletin A84-57-19,
Revision A, dated February 6, 2008.
(4) If two barrel nuts having no cracking are found and are on
opposite sides, within 100 flight hours after doing the inspection
required by paragraph (f)(2)(ii) of this AD, repeat the inspection
specified in paragraph (f)(2) of this AD. Thereafter, repeat the
inspection at intervals not to exceed 100 flight hours until the
replacement of all hardware at those locations is done. Do the
inspection and replacement in accordance with the Accomplishment
Instructions of Bombardier Alert Service Bulletin A84-57-19,
Revision A, dated February 6, 2008.
(5) If one barrel nut having no cracking is found, within 100
flight hours after doing the inspection required by paragraph
(f)(2)(ii) of this AD, repeat the inspection specified in paragraph
(f)(2) of this AD. Thereafter, repeat the inspection at intervals
not to exceed 100 flight hours until the replacement of all hardware
at that location is done. Do the inspection and replacement in
accordance with the Accomplishment Instructions of Bombardier Alert
Service Bulletin A84-57-19, Revision A, dated February 6, 2008.
Optional Replacement
(h) Replacement of all hardware for all barrel nuts, part number
DSC228-16, identified with a marking of LH7940T SPS 01, constitutes
terminating action for this AD. Replacement must be done in
accordance with the Accomplishment Instructions of Bombardier Alert
Service Bulletin A84-57-19, Revision A, dated February 6, 2008.
Actions Accomplished According to Previous Issue of Alert Service
Bulletin
(i) Actions accomplished before the effective date of this AD in
accordance with Bombardier Alert Service Bulletin A84-57-19, dated
February 1, 2008, are acceptable for compliance with the
corresponding actions specified in this AD.
Actions Accomplished According to Bombardier Alert Service Bulletin
A84-57-18
(j) For airplanes on which the actions specified in Bombardier
Alert Service Bulletin A84-57-18, dated January 16, 2008, were
accomplished before the effective date of this AD and on which no
barrel nuts were found that were identified with a marking of
LH7940T SPS 01: No further action is required by this AD.
Parts Installation
(k) As of the effective date of this AD, no person may install a
barrel nut, part number DSC228-16, identified with a marking of
LH7940T SPS 01, on any airplane.
Special Flight Permit
(l) Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), may be issued to operate the airplane to a location
where the requirements of this AD can be accomplished but
concurrence by the Manager, New York Aircraft Certification Office,
FAA, is required prior to issuance of the special flight permit.
Before using any approved special flight permits, notify your
appropriate principal inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your local FSDO. Special
flight permits may be permitted provided that the conditions
specified in paragraph (l)(1), (l)(2), (l)(3), (l)(4), and (l)(5) of
this AD are met.
(1) Both the right-hand side and left-hand side of the airplane
must have at least one barrel nut that is not within the suspect
batch (i.e., barrel nut is not identified with a marking of LH7940T
SPS 01). The barrel nuts that are not within the suspect batch must
be in good working condition (i.e., no cracking of the barrel nut).
(2) No passengers and no cargo are onboard.
(3) Airplane must operate in fair weather conditions with a low
risk of turbulence.
(4) Airplane must operate with reduced airspeed. For further
information, contact Bombardier, Q Series 24 Hour Service Customer
Response Center, at: Tel: 1-416-375-4000; Fax: 1-416-375-4539; E-
mail: thd.qseries@aero.bombardier.com.
(5) All of the conditions specified in paragraphs (l)(1),
(l)(2), (l)(3), and (l)(4) of this AD are on a case-by-case basis.
Contact your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO,
for assistance.
Alternative Methods of Compliance (AMOCs)
(m)(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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(n) Canadian emergency airworthiness directive CF-2008-11, dated
February 5, 2008.
Material Incorporated by Reference
(o) You must use Bombardier Alert Service Bulletin A84-57-19,
Revision A, dated February 6, 2008, to perform the actions that are
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register approved the incorporation by reference of
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123
Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for a copy of
this service information. You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.
Issued in Renton, Washington, on February 7, 2008.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-2747 Filed 2-12-08; 8:45 am]
BILLING CODE 4910-13-P
