Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 51903-51906 [E8-19718]
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Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations
MAXIMUM TURKEY INSPECTION RATES
Birds/minute
Line configuration
Inspection system
Number of
inspectors
J-Type
(>16#) 1
heavy
(<16#)
light
NTI–1
NTI–2
NTI–1
NTI–2
.........................................................................
.........................................................................
Modified ...........................................................
Modified ...........................................................
1 This
2 The
1
2
1
2
12–1
2 24–2
32
51
—
—
30
41
—
—
(>16#) 1
heavy
(<16#)
light
25
45
32
51
21
35
30
41
weight refers to the bird at the point of post-mortem inspection without blood or feet.
turkeys are suspended on the slaughter line at 12-inch intervals with two inspectors each looking at alternating birds at 24-inch intervals.
Done in Washington, DC, on August 29,
2008.
Alfred V. Almanza,
Administrator.
[FR Doc. E8–20551 Filed 9–5–08; 8:45 am]
BILLING CODE 3410–DM–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0356; Directorate
Identifier 2008–NM–042–AD; Amendment
39–15661; AD 2008–18–04]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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12–1
2 24–2
Bar-Type
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Jkt 214001
For service information
identified in this AD, contact
Bombardier, Inc., Bombardier Regional
Aircraft Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada.
ADDRESSES:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Bombardier
Model DHC–8–400 series airplanes.
That AD currently 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, the existing AD requires doing
repetitive visual inspections for
cracking of the barrel nuts and cradles
and replacing all hardware for all
cracked barrel nuts. The existing AD
also requires replacing all hardware for
certain affected barrel nuts that do not
have cracking, which would end the
repetitive inspections for those
airplanes. The existing AD also provides
an optional replacement for all affected
barrel nuts. This new AD requires
replacing all affected barrel nuts and
applying a certain compound to the
affected barrel nuts and bolts. This AD
results from reports of cracking in the
VerDate Aug<31>2005
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
October 14, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of October 14, 2008.
On February 13, 2008 (73 FR 8187,
February 13, 2008), the Director of the
Federal Register approved the
incorporation by reference of
Bombardier Alert Service Bulletin A84–
57–19, Revision A, dated February 6,
2008.
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 address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
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.
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SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that supersedes AD 2008–04–02,
amendment 39–15374 (73 FR 8187,
February 13, 2008). The existing AD
applies to certain Bombardier Model
DHC–8–400 series airplanes. That
supplemental NPRM was published in
the Federal Register on June 26, 2008
(73 FR 36285). That supplemental
NPRM proposed to continue to require
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, that supplemental
NPRM also proposed to continue to
require doing repetitive visual
inspections for cracking of the barrel
nuts and cradles and replacing all
hardware for all cracked barrel nuts.
That supplemental NPRM also proposed
to continue to require replacing all
hardware for certain affected barrel nuts
that do not have cracking, which would
end the repetitive inspections for those
airplanes. In addition, that
supplemental NPRM also proposed to
continue to provide an optional
replacement for all affected barrel nuts.
Finally, that supplemental NPRM also
proposed to require replacing all
affected barrel nuts and applying a
certain compound to the affected barrel
nuts and bolts.
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been received on the NPRM or on
the determination of the cost to the
public.
Conclusion
We have carefully reviewed the
available data and determined that air
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Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
This AD affects about 48 airplanes of
U.S. registry.
The actions that are required by AD
2008–04–02 and retained in this AD
take about 3 work hours per airplane, at
an average labor rate of $80 per work
hour. Based on these figures, the
estimated cost of the currently required
actions is $11,520, or $240 per airplane,
per inspection cycle.
Replacement of the hardware of a
barrel nut, if required, takes about 12
work hours per airplane, at an average
labor rate of $80 per work hour.
Required parts cost about $800 per
barrel nut. Based on these figures, we
estimate the cost of a replacement to be
$1,760 per barrel nut.
Application of the compound, if
required, takes about 4 work hours per
airplane, at an average labor rate of $80
per work hour. Based on these figures,
we estimate the cost of a replacement to
be $320 per application.
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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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 removing amendment 39–15374 (73
FR 8187, February 13, 2008) and by
adding the following new airworthiness
directive (AD):
I
2008–18–04 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–15661.
Docket No. FAA–2008–0356; Directorate
Identifier 2008–NM–042–AD.
Effective Date
(a) This AD becomes effective October 14,
2008.
Affected ADs
(b) This AD supersedes AD 2008–04–02.
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
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the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2008–
04–02 With New Service Information
Inspections and Corrective Actions
(f) Within 50 flight hours after February 13,
2008 (the effective date of AD 2008–04–02),
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; or Revision B,
dated March 6, 2008. As of the effective date
of this AD, Bombardier Alert Service Bulletin
A84–57–19, Revision B, dated March 6, 2008,
must be used.
(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; or Revision B, dated March
6, 2008. As of the effective date of this AD,
Bombardier Alert Service Bulletin A84–57–
19, Revision B, dated March 6, 2008, must be
used.
(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 pre-load 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
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Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations
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; or Revision B,
dated March 6, 2008. As of the effective date
of this AD, Bombardier Alert Service Bulletin
A84–57–19, Revision B, dated March 6, 2008,
must be used. 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; or
Revision B, dated March 6, 2008. As of the
effective date of this AD, Bombardier Alert
Service Bulletin A84–57–19, Revision B,
dated March 6, 2008, must be used.
(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; or Revision B, dated March
6, 2008. As of the effective date of this AD,
Bombardier Alert Service Bulletin A84–57–
19, Revision B, dated March 6, 2008, must be
used. 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; or
Revision B, dated March 6, 2008. As of the
effective date of this AD, Bombardier Alert
VerDate Aug<31>2005
17:07 Sep 05, 2008
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Service Bulletin A84–57–19, Revision B,
dated March 6, 2008, must be used.
(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.
(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; or
Revision B, dated March 6, 2008. As of the
effective date of this AD, Bombardier Alert
Service Bulletin A84–57–19, Revision B,
dated March 6, 2008, must be used.
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; or
Revision B, dated March 6, 2008. As of the
effective date of this AD, Bombardier Alert
Service Bulletin A84–57–19, Revision B,
dated March 6, 2008, must be used.
(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; or
Revision B, dated March 6, 2008. As of the
effective date of this AD, Bombardier Alert
Service Bulletin A84–57–19, Revision B,
dated March 6, 2008, must be used.
(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; or
Revision B, dated March 6, 2008. As of the
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51905
effective date of this AD, Bombardier Alert
Service Bulletin A84–57–19, Revision B,
dated March 6, 2008, must be used.
Actions Accomplished According to
Previous Issue of Alert Service Bulletin
(h) Actions accomplished before February
13, 2008, 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
(i) For airplanes on which the actions
specified in Bombardier Alert Service
Bulletin A84–57–18, dated January 16, 2008,
were accomplished before February 13, 2008,
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
(j) As of February 13, 2008, no person may
install a barrel nut, part number DSC228–16,
identified with a marking of LH7940T SPS
01, on any airplane.
New Requirement of This AD
Replacement of All Affected Barrel Nuts
(k) For airplanes on which barrel nuts are
inspected in accordance with paragraph
(g)(1)(iii), (g)(2)(iii), (g)(3)(iii), (g)(4), or (g)(5)
of this AD: Within 3,000 flight hours after the
effective date of this AD, replace all hardware
for all remaining barrel nuts, part number
DSC228–16, identified with a marking of
LH7940T SPS 01. Do the replacement in
accordance with the Accomplishment
Instructions of Bombardier Alert Service
Bulletin A84–57–19, Revision B, dated
March 6, 2008. Replacement of all hardware
for all affected barrel nuts constitutes
terminating action for the repetitive
inspections of this AD.
(l) For airplanes on which hardware for the
barrel nut was replaced in accordance with
Bombardier Alert Service Bulletin A84–57–
19, dated February 1, 2008; or Revision A,
dated February 6, 2008: Within 3,000 flight
hours after the effective date of this AD,
apply F13, Type 2 corrosion inhibiting
compound to the affected bolts and barrel
nuts in accordance with the Accomplishment
Instructions of Bombardier Alert Service
Bulletin A84–57–19, Revision B, dated
March 6, 2008; except if it can be
conclusively determined from a review of
airplane maintenance records that F13, Type
2 corrosion inhibiting compound was
applied to the affected bolts and barrel nuts,
then no further action is required by this
paragraph.
Special Flight Permit
(m) 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 (ACO), FAA, is
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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 paragraphs (m)(1),
(m)(2), (m)(3), (m)(4), and (m)(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: Telephone 1–
416–375–4000; fax 1–416–375–4539; E-mail:
thd.qseries@aero.bombardier.com.
(5) All of the conditions specified in
paragraphs (m)(1), (m)(2), (m)(3), and (m)(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)
(n)(1) The Manager, New York ACO, 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:
Pong Lee, Aerospace Engineer, Airframe and
Propulsion Branch, ANE–171, FAA, New
York ACO, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone (516)
228–7324; fax (516) 794–5531. 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.
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Related Information
(o) Canadian airworthiness directive CF–
2008–11R1, dated May 9, 2008, also
addresses the subject of the AD.
Material Incorporated by Reference
(p) You must use Bombardier Alert Service
Bulletin A84–57–19, Revision A, dated
February 6, 2008; or Bombardier Alert
Service Bulletin A84–57–19, Revision B,
dated March 6, 2008; as applicable; to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Bombardier Alert Service Bulletin A84–57–
19, Revision B, dated March 6, 2008, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On February 13, 2008 (73 FR 8187,
February 13, 2008), the Director of the
Federal Register approved the incorporation
by reference of Bombardier Alert Service
VerDate Aug<31>2005
17:07 Sep 05, 2008
Jkt 214001
Bulletin A84–57–19, Revision A, dated
February 6, 2008.
(3) 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 August
18, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–19718 Filed 9–5–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0672; Directorate
Identifier 2008–NM–032–AD; Amendment
39–15660; AD 2008–18–03]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200, A330–300, and A340–300
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
During manufacturing of A330/A340
aircraft framework, cracks have been found
on Frame (FR) 12, left (LH) and right (RH)
sides. It has been confirmed that a defect of
the FR12 forming tool press is the root cause
of the cracks.
If undetected such damage could affect,
after propagation, the structural integrity of
the aircraft.
*
*
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
October 14, 2008.
The Director of the Federal Register
approved the incorporation by reference
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
of certain publications listed in this AD
as of October 14, 2008.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on June 24, 2008 (73 FR 35595).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
During manufacturing of A330/A340
aircraft framework, cracks have been found
on Frame (FR) 12, left (LH) and right (RH)
sides. It has been confirmed that a defect of
the FR12 forming tool press is the root cause
of the cracks.
If undetected such damage could affect,
after propagation, the structural integrity of
the aircraft.
In order to permit an early detection and
repair of cracks on FR12, LH and RH sides,
this Airworthiness Directive (AD) mandates a
one time High Frequency Eddy Current
(HFEC) inspection of FR12.
Corrective actions include, for certain
findings, contacting Airbus for repair
instructions and doing the repair;
repairing cracking (i.e., installing a new
splice); and applying new protective
coatings and corrosion inhibitors. You
may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
E:\FR\FM\08SER1.SGM
08SER1
]]>Agencies
[Federal Register Volume 73, Number 174 (Monday, September 8, 2008)]
[Rules and Regulations]
[Pages 51903-51906]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-19718]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0356; Directorate Identifier 2008-NM-042-AD;
Amendment 39-15661; AD 2008-18-04]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Bombardier Model DHC-8-400 series
airplanes. That AD currently 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, the existing AD requires doing
repetitive visual inspections for cracking of the barrel nuts and
cradles and replacing all hardware for all cracked barrel nuts. The
existing AD also requires replacing all hardware for certain affected
barrel nuts that do not have cracking, which would end the repetitive
inspections for those airplanes. The existing AD also provides an
optional replacement for all affected barrel nuts. This new AD requires
replacing all affected barrel nuts and applying a certain compound to
the affected barrel nuts and bolts. 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 October 14, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of October 14,
2008.
On February 13, 2008 (73 FR 8187, February 13, 2008), the Director
of the Federal Register approved the incorporation by reference of
Bombardier Alert Service Bulletin A84-57-19, Revision A, dated February
6, 2008.
ADDRESSES: 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 address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
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
The FAA issued a supplemental notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an AD that supersedes AD 2008-04-02,
amendment 39-15374 (73 FR 8187, February 13, 2008). The existing AD
applies to certain Bombardier Model DHC-8-400 series airplanes. That
supplemental NPRM was published in the Federal Register on June 26,
2008 (73 FR 36285). That supplemental NPRM proposed to continue to
require 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, that
supplemental NPRM also proposed to continue to require doing repetitive
visual inspections for cracking of the barrel nuts and cradles and
replacing all hardware for all cracked barrel nuts. That supplemental
NPRM also proposed to continue to require replacing all hardware for
certain affected barrel nuts that do not have cracking, which would end
the repetitive inspections for those airplanes. In addition, that
supplemental NPRM also proposed to continue to provide an optional
replacement for all affected barrel nuts. Finally, that supplemental
NPRM also proposed to require replacing all affected barrel nuts and
applying a certain compound to the affected barrel nuts and bolts.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been received on the NPRM or
on the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air
[[Page 51904]]
safety and the public interest require adopting the AD as proposed.
Costs of Compliance
This AD affects about 48 airplanes of U.S. registry.
The actions that are required by AD 2008-04-02 and retained in this
AD take about 3 work hours per airplane, at an average labor rate of
$80 per work hour. Based on these figures, the estimated cost of the
currently required actions is $11,520, or $240 per airplane, per
inspection cycle.
Replacement of the hardware of a barrel nut, if required, takes
about 12 work hours per airplane, at an average labor rate of $80 per
work hour. Required parts cost about $800 per barrel nut. Based on
these figures, we estimate the cost of a replacement to be $1,760 per
barrel nut.
Application of the compound, if required, takes about 4 work hours
per airplane, at an average labor rate of $80 per work hour. Based on
these figures, we estimate the cost of a replacement to be $320 per
application.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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
removing amendment 39-15374 (73 FR 8187, February 13, 2008) and by
adding the following new airworthiness directive (AD):
2008-18-04 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-15661. Docket No. FAA-2008-0356; Directorate Identifier 2008-NM-
042-AD.
Effective Date
(a) This AD becomes effective October 14, 2008.
Affected ADs
(b) This AD supersedes AD 2008-04-02.
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.
Restatement of Requirements of AD 2008-04-02 With New Service
Information
Inspections and Corrective Actions
(f) Within 50 flight hours after February 13, 2008 (the
effective date of AD 2008-04-02), 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; or Revision B, dated
March 6, 2008. As of the effective date of this AD, Bombardier Alert
Service Bulletin A84-57-19, Revision B, dated March 6, 2008, must be
used.
(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; or Revision B, dated March 6, 2008. As of the
effective date of this AD, Bombardier Alert Service Bulletin A84-57-
19, Revision B, dated March 6, 2008, must be used.
(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 pre-load 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
[[Page 51905]]
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; or
Revision B, dated March 6, 2008. As of the effective date of this
AD, Bombardier Alert Service Bulletin A84-57-19, Revision B, dated
March 6, 2008, must be used. 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; or Revision B, dated March 6,
2008. As of the effective date of this AD, Bombardier Alert Service
Bulletin A84-57-19, Revision B, dated March 6, 2008, must be used.
(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; or Revision B, dated March 6,
2008. As of the effective date of this AD, Bombardier Alert Service
Bulletin A84-57-19, Revision B, dated March 6, 2008, must be used.
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; or Revision B, dated March 6,
2008. As of the effective date of this AD, Bombardier Alert Service
Bulletin A84-57-19, Revision B, dated March 6, 2008, must be used.
(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.
(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; or Revision B, dated March 6, 2008. As of the
effective date of this AD, Bombardier Alert Service Bulletin A84-57-
19, Revision B, dated March 6, 2008, must be used. 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; or Revision B, dated March 6,
2008. As of the effective date of this AD, Bombardier Alert Service
Bulletin A84-57-19, Revision B, dated March 6, 2008, must be used.
(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; or Revision B, dated March 6,
2008. As of the effective date of this AD, Bombardier Alert Service
Bulletin A84-57-19, Revision B, dated March 6, 2008, must be used.
(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; or
Revision B, dated March 6, 2008. As of the effective date of this
AD, Bombardier Alert Service Bulletin A84-57-19, Revision B, dated
March 6, 2008, must be used.
Actions Accomplished According to Previous Issue of Alert Service
Bulletin
(h) Actions accomplished before February 13, 2008, 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
(i) For airplanes on which the actions specified in Bombardier
Alert Service Bulletin A84-57-18, dated January 16, 2008, were
accomplished before February 13, 2008, 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
(j) As of February 13, 2008, no person may install a barrel nut,
part number DSC228-16, identified with a marking of LH7940T SPS 01,
on any airplane.
New Requirement of This AD
Replacement of All Affected Barrel Nuts
(k) For airplanes on which barrel nuts are inspected in
accordance with paragraph (g)(1)(iii), (g)(2)(iii), (g)(3)(iii),
(g)(4), or (g)(5) of this AD: Within 3,000 flight hours after the
effective date of this AD, replace all hardware for all remaining
barrel nuts, part number DSC228-16, identified with a marking of
LH7940T SPS 01. Do the replacement in accordance with the
Accomplishment Instructions of Bombardier Alert Service Bulletin
A84-57-19, Revision B, dated March 6, 2008. Replacement of all
hardware for all affected barrel nuts constitutes terminating action
for the repetitive inspections of this AD.
(l) For airplanes on which hardware for the barrel nut was
replaced in accordance with Bombardier Alert Service Bulletin A84-
57-19, dated February 1, 2008; or Revision A, dated February 6,
2008: Within 3,000 flight hours after the effective date of this AD,
apply F13, Type 2 corrosion inhibiting compound to the affected
bolts and barrel nuts in accordance with the Accomplishment
Instructions of Bombardier Alert Service Bulletin A84-57-19,
Revision B, dated March 6, 2008; except if it can be conclusively
determined from a review of airplane maintenance records that F13,
Type 2 corrosion inhibiting compound was applied to the affected
bolts and barrel nuts, then no further action is required by this
paragraph.
Special Flight Permit
(m) 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
(ACO), FAA, is
[[Page 51906]]
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 paragraphs
(m)(1), (m)(2), (m)(3), (m)(4), and (m)(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: Telephone 1-416-375-4000; fax 1-416-375-4539;
E-mail: thd.qseries@aero.bombardier.com.
(5) All of the conditions specified in paragraphs (m)(1),
(m)(2), (m)(3), and (m)(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)
(n)(1) The Manager, New York ACO, 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: Pong Lee, Aerospace
Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York
ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590;
telephone (516) 228-7324; fax (516) 794-5531. 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
(o) Canadian airworthiness directive CF-2008-11R1, dated May 9,
2008, also addresses the subject of the AD.
Material Incorporated by Reference
(p) You must use Bombardier Alert Service Bulletin A84-57-19,
Revision A, dated February 6, 2008; or Bombardier Alert Service
Bulletin A84-57-19, Revision B, dated March 6, 2008; as applicable;
to perform the actions that are required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Bombardier Alert Service Bulletin A84-
57-19, Revision B, dated March 6, 2008, in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On February 13, 2008 (73 FR 8187, February 13, 2008), the
Director of the Federal Register approved the incorporation by
reference of Bombardier Alert Service Bulletin A84-57-19, Revision
A, dated February 6, 2008.
(3) 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 August 18, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-19718 Filed 9-5-08; 8:45 am]
BILLING CODE 4910-13-P
