Airworthiness Directives; Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 Series Airplanes, 38575-38578 [05-12837]
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Federal Register / Vol. 70, No. 127 / Tuesday, July 5, 2005 / Rules and Regulations
Note 1: 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.’’
Issued in Renton, Washington, on June 21,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–12836 Filed 7–1–05; 8:45 am]
Corrective Action for Chafing Damage
Federal Aviation Administration
(h) If any chafing damage that is greater
than 0.2 mm is found during any inspection
required by paragraph (g)(1) of this AD,
replace the drive rod in accordance with the
service bulletin, at the applicable threshold
limits defined in the service bulletin.
Corrective Action for Discrepant Clearance
Measurements
(i) If any clearance measurement that is
outside the limits defined in the service
bulletin is found during the action required
by paragraph (g)(2) of this AD, do the actions
in paragraphs (i)(1) and (i)(2) of this AD. Do
all actions in accordance with the service
bulletin at the applicable threshold limits
defined in the service bulletin.
(1) Replace the polyamide washer or
replace the bush assembly.
(2) Do all applicable related investigative
and corrective actions after the replacement
in paragraph (i)(1) of this AD, including
replacing the aileron actuator with a
serviceable aileron actuator as applicable.
Alternative Methods of Compliance
(AMOCs)
(j) The Manager, International Branch,
ANM–116, FAA, Transport Airplane
Directorate, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
Related Information
(k) Dutch airworthiness directive 2003–
141, dated November 28, 2003, also
addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Fokker Service Bulletin
SBF100–27–083, dated October 20, 2003, to
perform the actions that are required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approves the
incorporation by reference of this document
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get copies of the service
information, contact Fokker Services B.V.,
P.O. Box 231, 2150 AE Nieuw-Vennep, the
Netherlands. To view the AD docket, go to
the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., room PL–401, Nassif Building,
Washington, DC. To review copies of the
service information, go to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
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14:45 Jul 01, 2005
Jkt 205001
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. FAA–2005–20852; Directorate
Identifier 2004–NM–240–AD; Amendment
39–14175; AD 2005–13–38]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–100, DHC–8–200, and
DHC–8–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier Model DHC–8–100, DHC–
8–200, and DHC–8–300 series airplanes.
This AD requires 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 also requires phase-in
inspections and repair of any crack
found during any phase-in inspection.
This 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 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.
DATES: This AD becomes effective
August 9, 2005.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of August 9, 2005.
ADDRESSES: For service information
identified in this AD, contact
Bombardier, Inc., Bombardier Regional
Aircraft Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada.
Docket: The AD docket contains the
proposed AD, comments, and any final
PO 00000
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38575
disposition. 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 U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
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: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Bombardier Model
DHC–8–100, DHC–8–200, and DHC–8–
300 series airplanes. That action,
published in the Federal Register on
April 6, 2005 (70 FR 17377), proposed
to 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. That AD also
proposed to require phase-in
inspections and repair of any crack
found during any phase-in inspection.
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been submitted on the proposed
AD or on the determination of the cost
to the public.
Explanation of Changes to the AD
We have revised the applicability of
the proposed AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
We have changed the references to the
Bombardier DHC–8 maintenance
program support manuals in Table 1 of
the proposed AD to reflect the way these
documents are referenced in the de
Havilland temporary revisions.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the changes
described previously. We have
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Federal Register / Vol. 70, No. 127 / Tuesday, July 5, 2005 / Rules and Regulations
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Action
Average
labor rate
per hour
Work hours
AWL revision ....................................................................
Phase-in inspection ..........................................................
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.
1
25
$65
65
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this 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, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
Regulatory Findings
§ 39.13
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
Cost per
airplane
Parts
I
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
2005–13–38 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–14175.
Docket No. FAA–2005–20852;
Directorate Identifier 2004-NM–240-AD.
Effective Date
(a) This AD becomes effective August 9,
2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to
Bombardier Model DHC–8–100, DHC–8–200,
and DHC–8–300 series airplanes; certificated
in any category; serial number 003 and
subsequent.
Note 1: This AD requires revisions to
certain operator maintenance documents to
N/A
N/A
$65
1,625
Number of
U.S.-registered airplanes
177
177
Fleet cost
$11,505
287,625
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 temporary revision (TR) listed
in Table 1 of this AD into the AWL section
of the applicable Bombardier DHC–8
Maintenance Program Support Manual
(PSM). 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
DHC–8 model
de Havilland TR
Dated
–102, –103, and –106 airplanes ................................................................
AWL–92 ................
June 28, 2004 .......
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For Bombardier DHC–8
maintenance Program
Support Manual
PSM 1–8–7.
Federal Register / Vol. 70, No. 127 / Tuesday, July 5, 2005 / Rules and Regulations
38577
TABLE 1.—TEMPORARY REVISIONS TO AWL—Continued
DHC–8 model
de Havilland TR
–201 and –202 airplanes ...........................................................................
–301, –311, and –315 airplanes ................................................................
Incorporation of TRs Into General Revisions
(g) When the information in the applicable
de Havilland 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 .............
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
Dated
June
June
June
June
June
28,
28,
28,
28,
28,
2004.
2004 .......
2004.
2004 .......
2004.
For Bombardier DHC–8
maintenance Program
Support Manual
PSM 1–82–7.
PSM 1–83–7.
longitudinal skin joints in the fuselage
pressure shell specified in the de Havilland
TR listed in Table 2 of this AD for the
applicable de Havilland maintenance task
card (MTC) in the specified MTC manual
section of the applicable Bombardier DHC–8
PSM.
TABLE 2.—TEMPORARY REVISIONS TO MTCS
DHC–8 model
de Havilland TR
–102, –103, and –106 airplanes .............................
MTC–45 .................
MTC–46 .................
MTC 2–45 ..............
MTC 2–46 ..............
MTC 3–47 ..............
MTC 3–48 ..............
–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
TR to the 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
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Dated
November
November
November
November
November
November
28,
28,
28,
28,
28,
28,
2003
2003
2003
2003
2003
2003
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 TR 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.
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Task No.
.......
.......
.......
.......
.......
.......
5310/29E .....
5310/30A.
5310/29E .....
5310/30A.
5310/29E .....
5310/30A.
For Bombardier DHC–8
maintenance program
support manual
PSM 1–8–7TC.
PSM 1–82–7TC.
PSM 1–83–7TC.
Related Information
(m) Canadian airworthiness directive CF–
2004–16, dated September 7, 2004, also
addresses the subject of this AD.
Material Incorporated by Reference
(n) You must use the applicable de
Havilland temporary revisions to the
applicable Bombardier DHC–8 Maintenance
Program Support Manual specified in Table
3 of this AD to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approves the incorporation by
reference of these documents in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To
get copies of the temporary revisions, contact
Bombardier, Inc., Bombardier Regional
Aircraft Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada. To
view the AD docket, go to the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC. To review copies of the temporary
revisions, go to the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
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Federal Register / Vol. 70, No. 127 / Tuesday, July 5, 2005 / Rules and Regulations
TABLE 3.—MATERIAL INCORPORATED BY REFERENCE
de Havilland temporary revision
Dated
AWL 2–31 ...............................................................................................................................
AWL 2–32 ...............................................................................................................................
AWL 3–98 ...............................................................................................................................
AWL 3–99 ...............................................................................................................................
AWL–92 ..................................................................................................................................
AWL–93 ..................................................................................................................................
MTC 2–45 ...............................................................................................................................
MTC 2–46 ...............................................................................................................................
MTC 3–47 ...............................................................................................................................
MTC 3–48 ...............................................................................................................................
MTC–45 ..................................................................................................................................
MTC–46 ..................................................................................................................................
June 28, 2004 ................
June 28, 2004.
June 28, 2004 ................
June 28, 2004.
June 28, 2004 ................
June 28, 2004.
November 28, 2003 .......
November 28, 2003.
November 28, 2003 .......
November 28, 2003.
November 28, 2003 .......
November 28, 2003.
Issued in Renton, Washington, on June 21,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–12837 Filed 7–1–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20872; Directorate
Identifier 2004–NM–271–AD; Amendment
39–14173; AD 2005–13–36]
RIN 2120–AA64
Airworthiness Directives; Learjet
Model 23, 24, 24A, 24B, 24B–A, 24C,
24D, 24D–A, 24E, 24F, 24F–A, 25, 25A,
25B, 25C, 25D, 25F, 28, 29, 31, 31A, 35,
35A (C–21A), and 36 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Learjet Model 23, 24, 24A, 24B, 24B–A,
24C, 24D, 24D–A, 24E, 24F, 24F–A, 25,
25A, 25B, 25C, 25D, 25F, 28, 29, 31,
31A, 35, 35A (C–21A), and 36 airplanes.
This AD requires a one-time inspection
of the center ball of the aileron control
cable or cables for a defective swage,
and corrective actions if necessary. This
AD is prompted by a report indicating
that an aileron cable failed on one
affected airplane when the cable
underwent a tension check. We are
issuing this AD to prevent severe
weakening of the aileron cable, and
consequent reduced controllability of
the airplane.
DATES: This AD becomes effective
August 9, 2005.
SUMMARY:
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The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of August 9, 2005.
ADDRESSES: For service information
identified in this AD, contact Learjet,
Inc., One Learjet Way, Wichita, Kansas
67209–2942.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. 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 U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
Washington, DC. This docket number is
FAA–2005–20872; the directorate
identifier for this docket is 2004–NM–
271–AD.
FOR FURTHER INFORMATION CONTACT:
David Hirt, Aerospace Engineer,
Systems and Propulsion Branch, ACE–
116W, FAA, Wichita Aircraft
Certification Office, 1801 Airport Road,
Room 100, Mid-Continent Airport,
Wichita, Kansas 67209; telephone (316)
946–4156; fax (316) 946–4107.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Learjet Model 23, 24,
24A, 24B, 24B–A, 24C, 24D, 24D–A,
24E, 24F, 24F–A, 25, 25A, 25B, 25C,
25D, 25F, 28, 29, 31, 31A, 35, 35A (C–
21A), and 36 airplanes. That action,
published in the Federal Register on
April 6, 2005 (70 FR 17349), proposed
to require a one-time inspection of the
center ball of the aileron control cable
or cables for a defective swage, and
corrective actions if necessary.
Comments
We provided the public the
opportunity to participate in the
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maintenance program
support manual
PSM 1–82–7.
PSM 1–83–7.
PSM 1–8–7.
PSM 1–82–7TC.
PSM 1–83–7TC.
PSM 1–8–7TC.
development of this AD. No comments
have been submitted on the proposed
AD or on the determination of the cost
to the public.
Clarification of Service Bulletin
References
All references to ‘‘Learjet Alert
Service Bulletins’’ have been changed to
refer to ‘‘Bombardier Alert Service
Bulletins.’’ This change more accurately
reflects the published titles of these
documents, and it is necessary to meet
the Office of the Federal Register’s
guidelines for material incorporated by
reference.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the change
described previously. We have
determined that this change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
There are about 1,704 airplanes of the
affected design in the worldwide fleet.
This AD affects about 1,136 airplanes of
U.S. registry. The inspection takes about
1 work hour per airplane, at an average
labor rate of $65 per work hour. Based
on these figures, the estimated cost of
the AD for U.S. operators is $73,840, or
$65 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
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]]>Agencies
[Federal Register Volume 70, Number 127 (Tuesday, July 5, 2005)]
[Rules and Regulations]
[Pages 38575-38578]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12837]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20852; Directorate Identifier 2004-NM-240-AD;
Amendment 39-14175; AD 2005-13-38]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-100, DHC-8-200,
and DHC-8-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 series
airplanes. This AD requires 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 also requires phase-in
inspections and repair of any crack found during any phase-in
inspection. This 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 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.
DATES: This AD becomes effective August 9, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of August
9, 2005.
ADDRESSES: For service information identified in this AD, contact
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. 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 U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
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: The FAA proposed to amend 14 CFR part 39
with an AD for certain Bombardier Model DHC-8-100, DHC-8-200, and DHC-
8-300 series airplanes. That action, published in the Federal Register
on April 6, 2005 (70 FR 17377), proposed to 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. That AD also
proposed to require phase-in inspections and repair of any crack found
during any phase-in inspection.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been submitted on the proposed
AD or on the determination of the cost to the public.
Explanation of Changes to the AD
We have revised the applicability of the proposed AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
We have changed the references to the Bombardier DHC-8 maintenance
program support manuals in Table 1 of the proposed AD to reflect the
way these documents are referenced in the de Havilland temporary
revisions.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD with the
changes described previously. We have
[[Page 38576]]
determined that these changes will neither increase the economic burden
on any operator nor increase the scope of the AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Average Cost per U.S.-
Action Work hours labor rate Parts airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
AWL revision...................... 1 $65 N/A $65 177 $11,505
Phase-in inspection............... 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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-13-38 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-14175. Docket No. FAA-2005-20852; Directorate Identifier 2004-NM-
240-AD.
Effective Date
(a) This AD becomes effective August 9, 2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to Bombardier Model DHC-8-
100, DHC-8-200, and DHC-8-300 series 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 temporary
revision (TR) listed in Table 1 of this AD into the AWL section of
the applicable Bombardier DHC-8 Maintenance Program Support Manual
(PSM). 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 Bombardier DHC-8
DHC-8 model de Havilland TR Dated maintenance Program Support
Manual
----------------------------------------------------------------------------------------------------------------
-102, -103, and -106 AWL-92................. June 28, 2004.......... PSM 1-8-7.
airplanes.
[[Page 38577]]
AWL-93................. June 28, 2004..........
-201 and -202 airplanes...... AWL 2-31............... June 28, 2004.......... PSM 1-82-7.
AWL 2-32............... June 28, 2004..........
-301, -311, and -315 AWL 3-98............... June 28, 2004.......... PSM 1-83-7.
airplanes.
AWL 3-99............... June 28, 2004..........
----------------------------------------------------------------------------------------------------------------
Incorporation of TRs Into General Revisions
(g) When the information in the applicable de Havilland 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 de Havilland TR listed in Table 2 of this AD for the applicable
de Havilland maintenance task card (MTC) in the specified MTC manual
section of the applicable Bombardier DHC-8 PSM.
Table 2.--Temporary Revisions to MTCs
--------------------------------------------------------------------------------------------------------------------------------------------------------
For Bombardier DHC-8 maintenance
DHC-8 model de Havilland TR Dated Task No. program support manual
--------------------------------------------------------------------------------------------------------------------------------------------------------
-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 TR to the 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 TR 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.
Material Incorporated by Reference
(n) You must use the applicable de Havilland temporary revisions
to the applicable Bombardier DHC-8 Maintenance Program Support
Manual specified in Table 3 of this AD to perform the actions that
are required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approves the incorporation by
reference of these documents in accordance with 5 U.S.C. 552(a) and
1 CFR part 51. To get copies of the temporary revisions, contact
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada. To view the AD
docket, go to the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC. To review copies of the temporary
revisions, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at the
NARA, call (202) 741-6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html.
[[Page 38578]]
Table 3.--Material Incorporated by Reference
--------------------------------------------------------------------------------------------------------------------------------------------------------
For Bombardier DHC-8 maintenance
de Havilland temporary revision Dated program support manual
------------------------------------------------------------------------------------------------------------------
AWL 2-31............................ June 28, 2004........................ PSM 1-82-7.
AWL 2-32............................ June 28, 2004........................
AWL 3-98............................ June 28, 2004........................ PSM 1-83-7.
AWL 3-99............................ June 28, 2004........................
AWL-92.............................. June 28, 2004........................ PSM 1-8-7.
AWL-93.............................. June 28, 2004........................
MTC 2-45............................ November 28, 2003.................... PSM 1-82-7TC.
MTC 2-46............................ November 28, 2003....................
MTC 3-47............................ November 28, 2003.................... PSM 1-83-7TC.
MTC 3-48............................ November 28, 2003....................
MTC-45.............................. November 28, 2003.................... PSM 1-8-7TC.
MTC-46.............................. November 28, 2003....................
--------------------------------------------------------------------------------------------------------------------------------------------------------
Issued in Renton, Washington, on June 21, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-12837 Filed 7-1-05; 8:45 am]
BILLING CODE 4910-13-P
