Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes, 17377-17381 [05-6770]
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Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701.
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. 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:
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15:58 Apr 05, 2005
Jkt 205001
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Fokker Services B.V.: Docket No. FAA–
2005–20868; Directorate Identifier 2004–
NM–162–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
May 6, 2005.
17377
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
Related Information
(i) Dutch airworthiness directive 2004–022,
dated February 27, 2004, also addresses the
subject of this AD.
Issued in Renton, Washington, on March
28, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–6771 Filed 4–5–05; 8:45 am]
BILLING CODE 4910–13–P
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Fokker Model
F.28 Mark 0100 series airplanes, certificated
in any category.
Unsafe Condition
(d) This AD was prompted by reported
incidents of smoke in the passenger
compartment during flight. One of those
incidents also included a burning smell and
consequently led to emergency evacuation of
the airplane. We are issuing this AD to
prevent overheating of the PSU panel due to
moisture ingress, which could result in
smoke or fire in the passenger cabin.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Inspection and Corrective Actions If
Applicable
(f) Within 36 months after the effective
date of this AD, inspect to determine if
Grimes Aerospace PSU panels having part
number (P/N) 10–1178–( ) or 10–1571–( )
are installed and the PSU modification status
if applicable, and do any corrective actions
if applicable, by doing all of the actions
specified in the Accomplishment
Instructions of Fokker Service Bulletin
SBF100–25–097, dated December 30, 2003.
Note 1: Fokker Service Bulletin SBF100–
25–097, dated December 30, 2003, refers to
Grimes Aerospace Service Bulletin 10–1178–
33–0040 (for PSU panel P/N 10–1178–( )),
Revision 1, dated March 25, 1996; and
Service Bulletin 10–1571–33–0041 (for PSU
panel P/N 10–1571–( )), dated October 15,
1993, as additional sources of service
information for modifying the PSU panel.
Parts Installation
(g) As of the effective date of this AD, no
person may install a PSU panel, P/Ns 10–
1178–( ) and 10–1571–( ), on any airplane,
unless it has been inspected and any
corrective actions if applicable have been
done in accordance with paragraph (f) of this
AD.
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20852; Directorate
Identifier 2004–NM–240–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–102, –103, –106, –201,
–202, –301, –311, and –315 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model DHC–8–102,
–103, –106, –201, –202, –301, –311, and
–315 airplanes. This proposed AD
would require revising the
airworthiness limitations section of the
Instructions for Continued
Airworthiness by incorporating new and
revised structural inspection procedures
and new and revised inspection
intervals for the longitudinal skin joints
in the fuselage pressure shell. This
proposed AD would also require phasein inspections and repair of any crack
found during any phase-in inspection.
This proposed AD is prompted by a
report indicating that visual inspections
were not adequate for detecting fatigue
cracking in portions of the longitudinal
skin joints in the fuselage pressure shell.
We are proposing this AD to detect and
correct fatigue cracking of the
longitudinal skin joints in the fuselage
pressure shell, which could affect the
structural integrity of the airplane, and
result in loss of cabin pressurization
during flight.
DATES: We must receive comments on
this proposed AD by May 6, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
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06APP1
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Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• By fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Bombardier,
Inc., Bombardier Regional Aircraft
Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20852; the directorate identifier for this
docket is 2004–NM–240–AD.
FOR FURTHER INFORMATION CONTACT:
David Lawson, 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) 228–7327; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES.
Include ‘‘Docket No. FAA–
2005–20852; Directorate Identifier
2004–NM–240–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments submitted by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of our docket
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You can
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
Discussion
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, notified us that an
unsafe condition may exist on certain
Bombardier Model DHC–8–102, –103,
–106, –201, –202, –301, –311, and –315
airplanes. TCCA advises that the
existing visual inspections in the
airworthiness limitations section of the
Instructions for Continued
Airworthiness were not adequate for
detecting fatigue cracking in portions of
the longitudinal skin joints in the
fuselage pressure shell. Those areas
were hidden by other structures. Fatigue
cracking of the fuselage longitudinal
skin joints, if not detected and
corrected, could affect the structural
integrity of the airplane, and result in
loss of cabin pressurization during
flight.
Explanation of Canadian Airworthiness
Directive and Relevant Service
Information
TCCA has issued Canadian
airworthiness directive CF–2004–16,
dated September 7, 2004, to ensure the
continued airworthiness of these
airplanes in Canada. The Canadian
airworthiness directive requires revising
the Transport Canada-approved
maintenance program by incorporating
new and revised structural inspection
procedures and new and revised
inspections intervals for the
longitudinal skin joints in the fuselage
pressure shell, as introduced in the
temporary revisions (TR) to the
applicable Bombardier DHC–8
Maintenance Program Manual, listed in
the following tables. The TRs to the
maintenance task cards (MTC) describe
new and revised structural inspections.
The TRs to the airworthiness limitations
(AWL) describe new structural
inspection intervals.
TABLE—TEMPORARY REVISIONS TO MTCS
Maintenance
program manual/program
support manual
(PSM)
DHC–8 model
–102, –103, –106 airplanes ......................................................
PSM 1–8–7TC
–201, –202 airplanes ................................................................
PSM 1–82–7TC
–301, –311, –315 airplanes ......................................................
PSM 1–83–7TC
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Frm 00039
Fmt 4702
Sfmt 4702
Temporary revision number
MTC–45
MTC–46
MTC 2–45
MTC 2–46
MTC 3–47
MTC 3–48
Task no.
5310/29E
5310/30A
5310/29E
5310/30A
5310/29E
5310/30A
E:\FR\FM\06APP1.SGM
06APP1
Date
November
November
November
November
November
November
28,
28,
28,
28,
28,
28,
2003.
2003.
2003.
2003.
2003.
2003.
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Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules
TABLE—TEMPORARY REVISIONS TO AWL
Maintenance program manual
DHC–8 model
–102,
–102,
–201,
–201,
–301,
–301,
–103, –106 airplanes ..................................................................................
–103, –106 airplanes ..................................................................................
–202 airplanes .............................................................................................
–202 airplanes .............................................................................................
–311, –315 airplanes ..................................................................................
–311, –315 airplanes ..................................................................................
PSM
PSM
PSM
PSM
PSM
PSM
1–8–7TC
1–8–7TC
1–82–7TC
1–82–7TC
1–83–7TC
1–83–7TC
Temporary
revision no.
AWL–92
AWL–93
AWL 2–31
AWL 2–32
AWL 3–98
AWL 3–99
Date
June
June
June
June
June
June
28,
28,
28,
28,
28,
28,
2004.
2004.
2004.
2004.
2004.
2004.
TABLE—RECOMMENDED COMPLIANCE TIMES IN TEMPORARY REVISIONS TO AWL
de Havilland, Inc., TR
AWL–92 ................................
AWL–92 ................................
AWL–93 ................................
AWL–93 ................................
AWL 2–31 ............................
AWL 2–32 ............................
AWL 3–98 ............................
AWL 3–99 ............................
AWL 3–99 ............................
DHC–8 model
airplanes
VerDate jul<14>2003
15:58 Apr 05, 2005
Action
–102 and –103
–106
–102 and –103
Detailed inspection .............
Detailed inspection .............
Above floor detailed inspection.
Below floor detailed inspection.
Above floor detailed inspection.
Below floor detailed inspection.
Detailed inspection .............
Above floor detailed inspection.
Below floor detailed inspection.
Detailed inspection .............
–106
–201 and –202
–201 and –202
–301, –311, and
–315
–301
Above floor detailed inspection.
Below floor detailed inspection.
Above floor detailed inspection.
Below floor detailed inspection.
–311 and –315
FAA’s Determination and Requirements
of the Proposed AD
These airplane models are
manufactured in Canada and are type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, TCCA has
kept the FAA informed of the situation
described above. We have examined
TCCA’s findings, evaluated all pertinent
information, and determined that we
need to issue an AD for products of this
type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD,
which would require revising the
airworthiness limitations section of the
Instructions for Continued
Airworthiness by incorporating new and
revised structural inspection procedures
Jkt 205001
Threshold/
initial inspection
(flight cycles)
40,000
40,000
80,000
37,000
36,240
16,475
40,000
40,000
80,000
10,980
40,000
40,000
80,000
9,350
40,000
20,346
60,346
6,230
40,000
40,000
Not applicable
40,000
40,000
80,000
36,240
9,350
40,000
20,346
60,346
6,230
40,000
Not applicable
40,000
36,240
40,000
Not applicable
40,000
40,000
40,000
Not applicable
40,000
30,920
40,000
Not applicable
40,000
40,000
40,000
Not applicable
40,000
33,933
The MTCs specify that you may
contact the manufacturer for
instructions on how to repair cracks in
the longitudinal skin joints in the
fuselage pressure shell, but this
proposed AD would require you to
repair those cracks using a method that
we or TCCA (or its delegated agent)
approve. In light of the type of repair
that would be required to address the
Fmt 4702
Sfmt 4702
Repetitive
intervals for
new
inspections
(flight cycles)
Not applicable
Not applicable
40,000
Differences Among the Proposed AD,
Canadian Airworthiness Directive, and
Service Information
Frm 00040
Phase-in
threshold/
new
inspections
(flight cycles)
40,000
40,000
40,000
and new and revised inspection
intervals for the longitudinal skin joints
in the fuselage pressure shell, except as
discussed under ‘‘Differences Between
the Proposed AD, Canadian
Airworthiness Directive, and Service
Information’’ This proposed AD would
also require phase-in inspections and
repair of any crack found during any
phase-in inspection.
PO 00000
Initial repetitive
inspection
(flight cycles)
unsafe condition, and consistent with
existing bilateral airworthiness
agreements, we have determined that,
for this proposed AD, a repair we or
TCCA approve would be acceptable for
compliance with this proposed AD.
Although the Canadian airworthiness
directive includes Bombardier Model
DHC–8–314 airplanes, the applicability
of this proposed AD does not include
that airplane model. That airplane
model is not included on the most
recent type certificate data sheet for the
affected models.
TCCA is aware of these differences.
Clarification of Inspection Terminology
In this proposed AD, the ‘‘detailed
visual inspection’’ specified in the
Bombardier temporary revision is
referred to as a ‘‘detailed inspection.’’
We have included the definition for a
detailed inspection in Note 1 of this
proposed AD.
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Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Work hours
AWL revision ......................................
Phase-in inspections ..........................
Average labor
rate per hour
1
25
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
$65
65
N/A .......................
N/A .......................
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Bombardier, Inc. (Formerly de Havilland,
Inc.): Docket No. FAA–2005–20852;
Directorate Identifier 2004–NM–240–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
May 6, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–102, –103, –106, –201, –202, –301,
–311, and –315 airplanes; certificated in any
category; serial number 003 and subsequent.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
Number of
U.S.-registered
airplanes
Cost per
airplane
Parts
$65
1,625
177
177
Fleet cost
$11,505
287,625
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance according
to paragraph (l) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued damage tolerance of the affected
structure. The FAA has provided guidance
for this determination in Advisory Circular
(AC) 25–1529.
Unsafe Condition
(d) This AD was prompted by a report
indicating that visual inspections were not
adequate for detecting fatigue cracking in
portions of the longitudinal skin joints in the
fuselage pressure shell. We are issuing this
AD to detect and correct fatigue cracking of
the longitudinal skin joints in the fuselage
pressure shell, which could affect the
structural integrity of the airplane, and result
in loss of cabin pressurization during flight.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Revision of Airworthiness Limitation (AWL)
Section
(f) Within 30 days after the effective date
of this AD: Revise the AWL section of the
Instructions for Continued Airworthiness by
incorporating the contents of the applicable
de Havilland, Inc., temporary revision (TR)
listed in Table 1 of this AD into the AWL
section of the applicable Bombardier DHC–8
Maintenance Program Support Manual.
Thereafter, except as provided by
paragraphs (g) and (l) of this AD, no
alternative structural inspection intervals
may be approved for the longitudinal skin
joints in the fuselage pressure shell.
TABLE 1.—TEMPORARY REVISIONS TO AWL
de Havilland, Inc.,
TR
DHC–8 model
–102, –103, and –106 airplanes ...........................................................................
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AWL–92
E:\FR\FM\06APP1.SGM
Dated
June 28, 2004
06APP1
For maintenance
program support
manual (PSM)
PSM 1–8–7TC
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Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules
TABLE 1.—TEMPORARY REVISIONS TO AWL—Continued
de Havilland, Inc.,
TR
DHC–8 model
–201 and –202 airplanes ......................................................................................
–301, –311, and –315 airplanes ...........................................................................
Incorporation of TRs Into General Revisions
(g) When the information in the applicable
de Havilland, Inc., TR identified in Table 1
of this AD has been included in the general
revisions of the applicable PSM identified in
Table 1 of this AD, the general revisions may
be inserted in the PSM, and the applicable
AWL–93
AWL 2–31
AWL 2–32
AWL 3–98
AWL 3–99
Dated
June
June
June
June
June
TR may be removed from the AWL section
of the Instruction for Continued
Airworthiness.
28,
28,
28,
28,
28,
2004
2004
2004
2004
2004
For maintenance
program support
manual (PSM)
PSM 1–82–7TC
PSM 1–83–7TC
current inspections, as applicable, of the
longitudinal skin joints in the fuselage
pressure shell specified in the TR for the
applicable Dash 8 (de Havilland, Inc.,)
maintenance task card (MTC) listed in Table
2 of this AD.
Phase-In Inspections
(h) At the times specified in paragraph (i)
of this AD, perform the detailed and eddy
TABLE 2.—TEMPORARY REVISIONS TO MTCS
de Havilland,
Inc., TR
DHC–8 model
–102, –103, and –106 airplanes ............................................
–201 and –202 airplanes .......................................................
–301, –311, and –315 airplanes ............................................
Note 2: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Compliance Times
(i) Perform the inspections required by
paragraph (h) of this AD at the applicable
time specified in paragraph (i)(1), (i)(2), or
(i)(3) of this AD.
(1) For all airplanes with 40,000 total flight
cycles or less as of the effective date of this
AD: At the times specified in the applicable
temporary revision to the Airworthiness
Limitations (AWL) listed in Table 1 of this
AD.
(2) For airplanes with more than 40,000
total flight cycles but less than 57,500 total
flight cycles as of the effective date of this
AD:
(i) For Model –102, –103, –301, –311, and
–315 airplanes: Within 5,000 flight hours
after the effective date of this AD or prior to
the accumulation of 60,000 total flight cycles,
whichever is first.
(ii) For Model –106, –201, and –202
airplanes: Within 5,000 flight hours after the
effective date of this AD or prior to the
accumulation of 60,346 total flight cycles,
whichever is first.
(3) For all airplanes with 57,500 total flight
cycles or more as of the effective date of this
AD: Within 12 months or 2,500 flight cycles
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MTC–45
MTC–46
MTC 2–45
MTC 2–46
MTC 3–47
MTC 3–48
Dated
November
November
November
November
November
November
28,
28,
28,
28,
28,
28,
after the effective date of this AD, whichever
is first.
(j) Repeat the inspections required by
paragraph (h) of this AD thereafter at the
intervals specified in the applicable
temporary revision to the AWL required by
paragraph (f) of this AD.
Repair
(k) If a crack is found in a longitudinal skin
joint during any phase-in inspection required
by paragraph (h) of this AD, and the MTC
specifies contacting Bombardier for repair
information: Before further flight, repair the
affected longitudinal skin joint in accordance
with a method approved by either the
Manager, New York ACO; or Transport
Canada Civil Aviation (or its delegated
agent).
AMOCs
(l) The Manager, New York ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
Related Information
(m) Canadian airworthiness directive CF–
2004–16, dated September 7, 2004, also
addresses the subject of this AD.
Issued in Renton, Washington, on March
29, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–6770 Filed 4–5–05; 8:45 am]
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5310/30A
For maintenance
program support
manual (PSM)
PSM 1–8–7TC
PSM 1–82–7TC
PSM 1–83–7TC
FEDERAL COMMUNICATIONS
COMMISSION
47 CFR Part 73
[DA 05–704; MB Docket No. 05–109, RM–
11192; MB Docket No. 05–110, RM–11193;
and MB Docket No. 05–111, RM–11200]
Radio Broadcasting Services;
Cumberland Head, NY; Mojave and
Trona, CA; and Haileyville and
Stringtown, OK
Federal Communications
Commission.
ACTION: Proposed rule.
AGENCY:
SUMMARY: This document sets forth
three proposals to amend the FM Table
of Allotments, Section 73.202(b) of the
Commission’s rules, 47 CFR 73.202(b).
The Commission requests comment on
a petition filed by Dana J. Puopolo.
Petitioner proposes the allotment of
Channel 255A at Mojave, California, as
a third local service. Channel 255A can
be allotted at Mojave in compliance
with the Commission’s minimum
distance separation requirements with a
site restriction of 10.3 km (6.4 miles)
northeast of Mojave. The proposed
coordinates for Channel 255A at Mojave
are 35–06–07 North Latitude and 118–
04–41 West Longitude. In addition, in
order to accommodate the allotment of
Channel 255A at Mojave, Petitioner
E:\FR\FM\06APP1.SGM
06APP1
]]>Agencies
[Federal Register Volume 70, Number 65 (Wednesday, April 6, 2005)]
[Proposed Rules]
[Pages 17377-17381]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6770]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20852; Directorate Identifier 2004-NM-240-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106,
-201, -202, -301, -311, and -315 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -
311, and -315 airplanes. This proposed AD would require revising the
airworthiness limitations section of the Instructions for Continued
Airworthiness by incorporating new and revised structural inspection
procedures and new and revised inspection intervals for the
longitudinal skin joints in the fuselage pressure shell. This proposed
AD would also require phase-in inspections and repair of any crack
found during any phase-in inspection. This proposed AD is prompted by a
report indicating that visual inspections were not adequate for
detecting fatigue cracking in portions of the longitudinal skin joints
in the fuselage pressure shell. We are proposing this AD to detect and
correct fatigue cracking of the longitudinal skin joints in the
fuselage pressure shell, which could affect the structural integrity of
the airplane, and result in loss of cabin pressurization during flight.
DATES: We must receive comments on this proposed AD by May 6, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
[[Page 17378]]
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
By fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada.
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street, SW., room PL-
401, on the plaza level of the Nassif Building, Washington, DC. This
docket number is FAA-2005-20852; the directorate identifier for this
docket is 2004-NM-240-AD.
FOR FURTHER INFORMATION CONTACT: David Lawson, 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) 228-7327; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-20852;
Directorate Identifier 2004-NM-240-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, notified us that an unsafe condition may exist on
certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311,
and -315 airplanes. TCCA advises that the existing visual inspections
in the airworthiness limitations section of the Instructions for
Continued Airworthiness were not adequate for detecting fatigue
cracking in portions of the longitudinal skin joints in the fuselage
pressure shell. Those areas were hidden by other structures. Fatigue
cracking of the fuselage longitudinal skin joints, if not detected and
corrected, could affect the structural integrity of the airplane, and
result in loss of cabin pressurization during flight.
Explanation of Canadian Airworthiness Directive and Relevant Service
Information
TCCA has issued Canadian airworthiness directive CF-2004-16, dated
September 7, 2004, to ensure the continued airworthiness of these
airplanes in Canada. The Canadian airworthiness directive requires
revising the Transport Canada-approved maintenance program by
incorporating new and revised structural inspection procedures and new
and revised inspections intervals for the longitudinal skin joints in
the fuselage pressure shell, as introduced in the temporary revisions
(TR) to the applicable Bombardier DHC-8 Maintenance Program Manual,
listed in the following tables. The TRs to the maintenance task cards
(MTC) describe new and revised structural inspections. The TRs to the
airworthiness limitations (AWL) describe new structural inspection
intervals.
Table--Temporary Revisions to MTCs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Maintenance program manual/
DHC-8 model program support manual Temporary revision Task no. Date
(PSM) number
--------------------------------------------------------------------------------------------------------------------------------------------------------
-102, -103, -106 airplanes........ PSM 1-8-7TC MTC-45 5310/29E November 28, 2003.
MTC-46 5310/30A November 28, 2003.
-201, -202 airplanes.............. PSM 1-82-7TC MTC 2-45 5310/29E November 28, 2003.
MTC 2-46 5310/30A November 28, 2003.
-301, -311, -315 airplanes........ PSM 1-83-7TC MTC 3-47 5310/29E November 28, 2003.
MTC 3-48 5310/30A November 28, 2003.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 17379]]
Table--Temporary Revisions to AWL
----------------------------------------------------------------------------------------------------------------
Temporary revision
DHC-8 model Maintenance program manual no. Date
----------------------------------------------------------------------------------------------------------------
-102, -103, -106 airplanes.... PSM 1-8-7TC AWL-92 June 28, 2004.
-102, -103, -106 airplanes.... PSM 1-8-7TC AWL-93 June 28, 2004.
-201, -202 airplanes.......... PSM 1-82-7TC AWL 2-31 June 28, 2004.
-201, -202 airplanes.......... PSM 1-82-7TC AWL 2-32 June 28, 2004.
-301, -311, -315 airplanes.... PSM 1-83-7TC AWL 3-98 June 28, 2004.
-301, -311, -315 airplanes.... PSM 1-83-7TC AWL 3-99 June 28, 2004.
----------------------------------------------------------------------------------------------------------------
Table--Recommended Compliance Times in Temporary Revisions to AWL
--------------------------------------------------------------------------------------------------------------------------------------------------------
Phase-in Repetitive
Threshold/ threshold/ intervals
initial Initial repetitive new for new
de Havilland, Inc., TR DHC-8 model airplanes Action inspection inspection (flight inspections inspections
(flight cycles) (flight (flight
cycles) cycles) cycles)
--------------------------------------------------------------------------------------------------------------------------------------------------------
AWL-92....................... -102 and -103 Detailed inspection............... 40,000 Not applicable 40,000 37,000
AWL-92....................... -106 Detailed inspection............... 40,000 Not applicable 40,000 36,240
AWL-93....................... -102 and -103 Above floor detailed inspection... 40,000 40,000 80,000 16,475
Below floor detailed inspection... 40,000 40,000 80,000 10,980
AWL-93....................... -106 Above floor detailed inspection... 40,000 40,000 80,000 9,350
Below floor detailed inspection... 40,000 20,346 60,346 6,230
AWL 2-31..................... -201 and -202 Detailed inspection............... 40,000 Not applicable 40,000 36,240
AWL 2-32..................... -201 and -202 Above floor detailed inspection... 40,000 40,000 80,000 9,350
Below floor detailed inspection... 40,000 20,346 60,346 6,230
AWL 3-98..................... -301, -311, and -315 Detailed inspection............... 40,000 Not applicable 40,000 36,240
AWL 3-99..................... -301 Above floor detailed inspection... 40,000 Not applicable 40,000 40,000
Below floor detailed inspection... 40,000 Not applicable 40,000 30,920
AWL 3-99..................... -311 and -315 Above floor detailed inspection... 40,000 Not applicable 40,000 40,000
Below floor detailed inspection... 40,000 Not applicable 40,000 33,933
--------------------------------------------------------------------------------------------------------------------------------------------------------
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in Canada and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, TCCA has kept the FAA informed of
the situation described above. We have examined TCCA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require revising
the airworthiness limitations section of the Instructions for Continued
Airworthiness by incorporating new and revised structural inspection
procedures and new and revised inspection intervals for the
longitudinal skin joints in the fuselage pressure shell, except as
discussed under ``Differences Between the Proposed AD, Canadian
Airworthiness Directive, and Service Information'' This proposed AD
would also require phase-in inspections and repair of any crack found
during any phase-in inspection.
Differences Among the Proposed AD, Canadian Airworthiness Directive,
and Service Information
The MTCs specify that you may contact the manufacturer for
instructions on how to repair cracks in the longitudinal skin joints in
the fuselage pressure shell, but this proposed AD would require you to
repair those cracks using a method that we or TCCA (or its delegated
agent) approve. In light of the type of repair that would be required
to address the unsafe condition, and consistent with existing bilateral
airworthiness agreements, we have determined that, for this proposed
AD, a repair we or TCCA approve would be acceptable for compliance with
this proposed AD.
Although the Canadian airworthiness directive includes Bombardier
Model DHC-8-314 airplanes, the applicability of this proposed AD does
not include that airplane model. That airplane model is not included on
the most recent type certificate data sheet for the affected models.
TCCA is aware of these differences.
Clarification of Inspection Terminology
In this proposed AD, the ``detailed visual inspection'' specified
in the Bombardier temporary revision is referred to as a ``detailed
inspection.'' We have included the definition for a detailed inspection
in Note 1 of this proposed AD.
[[Page 17380]]
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
AWL revision.............................. 1 $65 N/A......................... $65 177 $11,505
Phase-in inspections...................... 25 65 N/A......................... 1,625 177 287,625
--------------------------------------------------------------------------------------------------------------------------------------------------------
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. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2005-
20852; Directorate Identifier 2004-NM-240-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by May 6, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-102, -103, -106, -
201, -202, -301, -311, and -315 airplanes; certificated in any
category; serial number 003 and subsequent.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (l) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued damage tolerance of the affected structure. The FAA
has provided guidance for this determination in Advisory Circular
(AC) 25-1529.
Unsafe Condition
(d) This AD was prompted by a report indicating that visual
inspections were not adequate for detecting fatigue cracking in
portions of the longitudinal skin joints in the fuselage pressure
shell. We are issuing this AD to detect and correct fatigue cracking
of the longitudinal skin joints in the fuselage pressure shell,
which could affect the structural integrity of the airplane, and
result in loss of cabin pressurization during flight.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Revision of Airworthiness Limitation (AWL) Section
(f) Within 30 days after the effective date of this AD: Revise
the AWL section of the Instructions for Continued Airworthiness by
incorporating the contents of the applicable de Havilland, Inc.,
temporary revision (TR) listed in Table 1 of this AD into the AWL
section of the applicable Bombardier DHC-8 Maintenance Program
Support Manual.
Thereafter, except as provided by paragraphs (g) and (l) of this
AD, no alternative structural inspection intervals may be approved
for the longitudinal skin joints in the fuselage pressure shell.
Table 1.--Temporary Revisions to AWL
----------------------------------------------------------------------------------------------------------------
For maintenance program
DHC-8 model de Havilland, Inc., TR Dated support manual (PSM)
----------------------------------------------------------------------------------------------------------------
-102, -103, and -106 airplanes AWL-92 June 28, 2004 PSM 1-8-7TC
[[Page 17381]]
AWL-93 June 28, 2004
-201 and -202 airplanes....... AWL 2-31 June 28, 2004 PSM 1-82-7TC
AWL 2-32 June 28, 2004
-301, -311, and -315 airplanes AWL 3-98 June 28, 2004 PSM 1-83-7TC
AWL 3-99 June 28, 2004
----------------------------------------------------------------------------------------------------------------
Incorporation of TRs Into General Revisions
(g) When the information in the applicable de Havilland, Inc.,
TR identified in Table 1 of this AD has been included in the general
revisions of the applicable PSM identified in Table 1 of this AD,
the general revisions may be inserted in the PSM, and the applicable
TR may be removed from the AWL section of the Instruction for
Continued Airworthiness.
Phase-In Inspections
(h) At the times specified in paragraph (i) of this AD, perform
the detailed and eddy current inspections, as applicable, of the
longitudinal skin joints in the fuselage pressure shell specified in
the TR for the applicable Dash 8 (de Havilland, Inc.,) maintenance
task card (MTC) listed in Table 2 of this AD.
Table 2.--Temporary Revisions to MTCs
--------------------------------------------------------------------------------------------------------------------------------------------------------
For maintenance program
DHC-8 model de Havilland, Inc., TR Dated Task No. support manual (PSM)
--------------------------------------------------------------------------------------------------------------------------------------------------------
-102, -103, and -106 airplanes.... MTC-45 November 28, 2003 5310/29E PSM 1-8-7TC
MTC-46 November 28, 2003 5310/30A
-201 and -202 airplanes........... MTC 2-45 November 28, 2003 5310/29E PSM 1-82-7TC
MTC 2-46 November 28, 2003 5310/30A
-301, -311, and -315 airplanes.... MTC 3-47 November 28, 2003 5310/29E PSM 1-83-7TC
MTC 3-48 November 28, 2003 5310/30A
--------------------------------------------------------------------------------------------------------------------------------------------------------
Note 2: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Compliance Times
(i) Perform the inspections required by paragraph (h) of this AD
at the applicable time specified in paragraph (i)(1), (i)(2), or
(i)(3) of this AD.
(1) For all airplanes with 40,000 total flight cycles or less as
of the effective date of this AD: At the times specified in the
applicable temporary revision to the Airworthiness Limitations (AWL)
listed in Table 1 of this AD.
(2) For airplanes with more than 40,000 total flight cycles but
less than 57,500 total flight cycles as of the effective date of
this AD:
(i) For Model -102, -103, -301, -311, and -315 airplanes: Within
5,000 flight hours after the effective date of this AD or prior to
the accumulation of 60,000 total flight cycles, whichever is first.
(ii) For Model -106, -201, and -202 airplanes: Within 5,000
flight hours after the effective date of this AD or prior to the
accumulation of 60,346 total flight cycles, whichever is first.
(3) For all airplanes with 57,500 total flight cycles or more as
of the effective date of this AD: Within 12 months or 2,500 flight
cycles after the effective date of this AD, whichever is first.
(j) Repeat the inspections required by paragraph (h) of this AD
thereafter at the intervals specified in the applicable temporary
revision to the AWL required by paragraph (f) of this AD.
Repair
(k) If a crack is found in a longitudinal skin joint during any
phase-in inspection required by paragraph (h) of this AD, and the
MTC specifies contacting Bombardier for repair information: Before
further flight, repair the affected longitudinal skin joint in
accordance with a method approved by either the Manager, New York
ACO; or Transport Canada Civil Aviation (or its delegated agent).
AMOCs
(l) The Manager, New York ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
Related Information
(m) Canadian airworthiness directive CF-2004-16, dated September
7, 2004, also addresses the subject of this AD.
Issued in Renton, Washington, on March 29, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-6770 Filed 4-5-05; 8:45 am]
BILLING CODE 4910-13-P
