[Federal Register: July 5, 2005 (Volume 70, Number 127)]
[Rules and Regulations]
[Page 38575-38578]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05jy05-3]
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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;
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.
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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
http://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
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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
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For Bombardier DHC-8
DHC-8 model de Havilland TR Dated maintenance Program Support
Manual
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-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..........
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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
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For Bombardier DHC-8 maintenance
DHC-8 model de Havilland TR Dated Task No. program support manual
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-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..............
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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 http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
[[Page 38578]]
Table 3.--Material Incorporated by Reference
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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....................
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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