Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 15682-15685 [E8-6054]
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15682
Federal Register / Vol. 73, No. 58 / Tuesday, March 25, 2008 / Proposed Rules
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 determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
rwilkins on PROD1PC63 with PROPOSALS
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
VerDate Aug<31>2005
16:26 Mar 24, 2008
Jkt 214001
§ 39.13
FAA AD Differences
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Airbus: Docket No. FAA–2008–0342;
Directorate Identifier 2007–NM–305–AD.
Comments Due Date
(a) We must receive comments by April 24,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318,
A319, A320, and A321 series airplanes,
certificated in any category, all certified
models; all serial numbers which have
received an original French standard
airworthiness certificate or original French
export certificate of airworthiness prior to
February 28, 2007, and have been fitted with
a cargo compartment fire extinguisher bottle
installed in production, or in service by an
Airbus Service Bulletin; except airplanes on
which Airbus (MRBR) Maintenance Review
Board Report Task 26.23.00/03 or 26.23.00/
07 has been performed.
Subject
(d) Air Transport Association (ATA) of
America Code 26: Fire Protection.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
During planned maintenance visit on one
A320 aircraft, a cross connection of the fire
extinguishing circuit system was identified.
In case of fire, this cross connection will
activate (discharge) the wrong forward or aft
cargo compartment fire extinguisher bottle.
Failure to activate the correct bottle when
required is classified as potentially
catastrophic.
For the reasons described above, this AD
requires a one-time inspection and check of
the cargo firing circuit continuity to confirm
the correct connection of the dedicated wires
between the discharge pushbutton switches
and the relevant cargo bottle.
Corrective action includes modifying the
wiring connection on plug 1505VC–A.
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
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, Transport Airplane
Directorate, 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: Tim Dulin,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2141; 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 2007–0249, dated September 24,
2007, and Airbus Service Bulletin A320–
26A1068, Revision 01, dated July 19, 2007,
for related information.
Issued in Renton, Washington, on March
14, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–6051 Filed 3–24–08; 8:45 am]
BILLING CODE 4910–13–P
Actions and Compliance
(f) Within 600 flight hours after the
effective date of this AD, unless already
done, perform the inspection and continuity
check of the cargo firing circuit and, before
next flight, do applicable corrective actions;
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
26A1068, Revision 01, dated July 19, 2007.
Actions done before the effective date of this
AD in accordance with Airbus Service
Bulletin A320–26A1068, dated March 19,
2007, are considered acceptable for
compliance with the requirements of this AD.
Accomplishing Airbus MRBR Task 26.23.00/
03 or 26.23.00/07 is an acceptable method of
compliance with the requirements of this AD.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0356; Directorate
Identifier 2008–NM–042–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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Federal Register / Vol. 73, No. 58 / Tuesday, March 25, 2008 / Proposed Rules
Notice of proposed rulemaking
(NPRM).
rwilkins on PROD1PC63 with PROPOSALS
ACTION:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Bombardier Model DHC–8–400 series
airplanes. The existing 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 preloaded 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 replacement of 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 proposed AD would
require replacement of all affected barrel
nuts. This proposed AD results from
reports of cracking in the barrel nuts at
the four primary front spar wing-tofuselage attachment joints. We are
proposing 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: We must receive comments on
this proposed AD by April 24, 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
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16:26 Mar 24, 2008
Jkt 214001
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed 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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0356; Directorate Identifier
2008–NM–042–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed 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 proposed AD.
Discussion
On February 7, 2008, we issued AD
2008–04–02, amendment 39–15374 (73
FR 8187, February 13, 2008), for certain
Bombardier Model DHC–8–400 series
airplanes. That 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, that AD requires doing
repetitive visual inspections for
cracking of the barrel nuts and cradles
and replacing all hardware for all
cracked barrel nuts. That 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. That AD also provides an
optional replacement for all affected
barrel nuts. That AD resulted from
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15683
reports of cracking in the barrel nuts at
the four primary front spar wing-tofuselage attachment joints. We issued
that 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.
Actions Since Existing AD Was Issued
The preamble to AD 2008–04–02
explains that we consider the
requirements ‘‘interim action’’ and were
considering further rulemaking to
require the replacement of all hardware
for all barrel nuts identified with a
marking of LH7940T SPS 01. We now
have determined that further
rulemaking is indeed necessary, and
this proposed AD follows from that
determination.
FAA’s Determination and Requirements
of the Proposed 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,
Transport Canada Civil Aviation (TCCA)
has kept the FAA informed of the
situation described above. We have
examined the TCCA’s findings,
evaluated all pertinent information, and
determined that AD action is necessary
for airplanes of this type design that are
certificated for operation in the United
States.
This proposed AD would supersede
AD 2008–04–02 and would retain the
requirements of the existing AD. This
proposed AD would also require
replacement of all affected barrel nuts.
Costs of Compliance
This proposed AD would affect about
48 airplanes of U.S. registry.
The actions that are required by AD
2008–04–02 and retained in this
proposed 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, will take about 12
work hours per airplane, at an average
labor rate of $80 per work hour.
Required parts will cost about $800 per
airplane. Based on these figures, we
estimate the cost of a replacement to be
$1,760 per barrel nut.
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15684
Federal Register / Vol. 73, No. 58 / Tuesday, March 25, 2008 / Proposed Rules
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
rwilkins on PROD1PC63 with PROPOSALS
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
VerDate Aug<31>2005
16:26 Mar 24, 2008
Jkt 214001
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 adding
the following new airworthiness
directive (AD):
Bombardier, Inc. (Formerly de Havilland,
Inc.): Docket No. FAA–2008–0356;
Directorate Identifier 2008–NM–042–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by April 24, 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
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.
(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 pre-load is correct, before further
flight, do a visual inspection for cracking of
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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
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rwilkins on PROD1PC63 with PROPOSALS
Federal Register / Vol. 73, No. 58 / Tuesday, March 25, 2008 / Proposed Rules
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.
(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
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16:26 Mar 24, 2008
Jkt 214001
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.
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 A, dated
February 6, 2008. Replacement of all
hardware for all affected barrel nuts
constitutes terminating action for this AD.
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).
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
15685
(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), (1)(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.
Issued in Renton, Washington, on March
17, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–6054 Filed 3–24–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2007–0092; Airspace
Docket No. 07–AAL–18]
RIN 2120–AA66
Proposed Establishment of Colored
and VOR Federal Airways; Alaska
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This action proposes to
establish four Federal airways in the
National Airspace System (NAS) to
replace four non-part 95 routes in
Alaska. The conversion of these nonpart 95 routes would change uncharted
nonregulatory airways requiring special
E:\FR\FM\25MRP1.SGM
25MRP1
]]>Agencies
[Federal Register Volume 73, Number 58 (Tuesday, March 25, 2008)]
[Proposed Rules]
[Pages 15682-15685]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-6054]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0356; Directorate Identifier 2008-NM-042-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 15683]]
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Bombardier Model DHC-8-400
series airplanes. The existing 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 replacement of 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
proposed AD would require replacement of all affected barrel nuts. This
proposed AD results from reports of cracking in the barrel nuts at the
four primary front spar wing-to-fuselage attachment joints. We are
proposing 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: We must receive comments on this proposed AD by April 24, 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 proposed 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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0356;
Directorate Identifier 2008-NM-042-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed 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 proposed AD.
Discussion
On February 7, 2008, we issued AD 2008-04-02, amendment 39-15374
(73 FR 8187, February 13, 2008), for certain Bombardier Model DHC-8-400
series airplanes. That 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, that AD requires doing repetitive visual
inspections for cracking of the barrel nuts and cradles and replacing
all hardware for all cracked barrel nuts. That 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. That AD also provides an optional replacement for all
affected barrel nuts. That AD resulted from reports of cracking in the
barrel nuts at the four primary front spar wing-to-fuselage attachment
joints. We issued that 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.
Actions Since Existing AD Was Issued
The preamble to AD 2008-04-02 explains that we consider the
requirements ``interim action'' and were considering further rulemaking
to require the replacement of all hardware for all barrel nuts
identified with a marking of LH7940T SPS 01. We now have determined
that further rulemaking is indeed necessary, and this proposed AD
follows from that determination.
FAA's Determination and Requirements of the Proposed 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, Transport Canada Civil Aviation
(TCCA) has kept the FAA informed of the situation described above. We
have examined the TCCA's findings, evaluated all pertinent information,
and determined that AD action is necessary for airplanes of this type
design that are certificated for operation in the United States.
This proposed AD would supersede AD 2008-04-02 and would retain the
requirements of the existing AD. This proposed AD would also require
replacement of all affected barrel nuts.
Costs of Compliance
This proposed AD would affect about 48 airplanes of U.S. registry.
The actions that are required by AD 2008-04-02 and retained in this
proposed 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, will take
about 12 work hours per airplane, at an average labor rate of $80 per
work hour. Required parts will cost about $800 per airplane. Based on
these figures, we estimate the cost of a replacement to be $1,760 per
barrel nut.
[[Page 15684]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-15374 (73 FR 8187, February 13, 2008) and adding
the following new airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2008-
0356; Directorate Identifier 2008-NM-042-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 24,
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
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.
(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 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 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
[[Page 15685]]
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.
(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.
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 A, dated February 6, 2008. Replacement of all
hardware for all affected barrel nuts constitutes terminating action
for this AD.
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),
(1)(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.
Issued in Renton, Washington, on March 17, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-6054 Filed 3-24-08; 8:45 am]
BILLING CODE 4910-13-P
