[Federal Register: September 7, 2004 (Volume 69, Number 172)]
[Rules and Regulations]
[Page 53999-54000]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07se04-1]
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Rules and Regulations
Federal Register
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[[Page 53999]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18563; Directorate Identifier 2002-NM-98-AD;
Amendment 39-13783; AD 2004-18-05]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-311 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier Model DHC-8-311 airplanes. This AD requires
reviewing the airplane maintenance records to determine if you did the
most recent bonding integrity inspection according to a certain
revision of the Maintenance Program Support Manual (PSM), and doing
related investigative and corrective actions if necessary. This AD is
prompted by the discovery that a certain revision of the PSM omits
several fuselage skin panels from a list of skin panels that must be
inspected. We are issuing this AD to prevent disbonding of the subject
skin panels, which could reduce the load-carrying capacity of the skin
panels and result in reduced structural integrity of the airplane.
DATES: This AD becomes effective October 12, 2004.
ADDRESSES: You can examine the contents of this AD docket on the
Internet at http://dms.dot.gov, or 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.
FOR FURTHER INFORMATION CONTACT: Technical information: Jon Hjelm,
Aerospace Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New
York Aircraft Certification Office, 1600 Stewart Avenue, Westbury, New
York 11590; telephone (516) 228-7323; fax (516) 794-5531.
Plain language information: Marcia Walters, marcia.walters@faa.gov.
Examining the 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 DOT
street address stated in the ADDRESSES section.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39
with an AD for certain Bombardier Model DHC-8-311 airplanes. The
proposed AD was published in the Federal Register on July 8, 2004 (69
FR 41213), to require reviewing the airplane maintenance records to
determine if you did the most recent bonding integrity inspection
according to a certain revision of the Maintenance Program Support
Manual (PSM), and doing related investigative and corrective actions if
necessary.
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.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
This AD will affect about 8 airplanes of U.S. registry. The records
review will take 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 proposed AD for U.S. operators is $520, or $65 per airplane.
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, 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:
2004-18-05 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-13783. Docket No. FAA-2004-18563; Directorate Identifier 2002-NM-
98-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
12, 2004.
Affected ADs
(b) None.
[[Page 54000]]
Applicability
(c) This AD applies to Model DHC-8-311 airplanes, serial numbers
202 through 298 inclusive, certificated in any category.
Unsafe Condition
(d) This AD was prompted by the discovery that a certain
revision of the Maintenance Program Support Manual (PSM) omits
several fuselage skin panels from a list of skin panels that must be
inspected. We are issuing this AD to prevent disbonding of the
subject skin panels, which could reduce the load-carrying capacity
of the skin panels and result in reduced structural integrity of the
airplane.
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.
Review of Maintenance Records
(f) Within 14 days after the effective date of this AD, review
the airplane maintenance records or maintenance logbook to determine
if the most recent bonding integrity inspection of the fuselage skin
panels was done according to Bombardier Maintenance Program Support
Manual (PSM) 1-83-7A, Revision 6, dated January 30, 2001.
(1) If it can conclusively be determined that the most recent
bonding integrity inspection of the fuselage skin panels was done
according to PSM 1-83-7A, Revision 5, dated April 30, 1999; or
Revision 7, dated August 15, 2001: This AD requires no further
action.
(2) If the most recent bonding integrity inspection of the
fuselage skin panels was done according to PSM 1-83-7A, Revision 6,
dated January 30, 2001, or if it cannot be conclusively determined
what revision of PSM 1-83-7A was used: At the applicable compliance
time specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, do a
resonance frequency inspection of the fuselage skin panels listed in
Table 1 of this AD, according to a method approved by either the
Manager, New York Aircraft Certification Office (ACO), FAA; or
Transport Canada Civil Aviation (TCCA) (or its delegated agent). PSM
1-83-7A, Revision 7, dated August 15, 2001, is one approved method.
(i) If no disbonding was found during any previous bonding
integrity inspection: Within 1,000 flight hours or 6 months after
the effective date of this AD, whichever is first.
(ii) If any disbonding was found during any previous bonding
integrity inspection: Within 6 weeks after the effective date of
this AD.
Table 1.--Fuselage Skin Panels
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Engineering drawing Skin panel description PSM 1-83-7A figure sheet
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85330204................................ Skin, Right Side, Bottom.... Figure 4/(Sheet 2).
85330201................................ Skin, Right Side............ Figure 4/(Sheet 5).
85330180................................ Skin, Right Side, Top....... Figure 4/(Sheet 6).
85330181................................ Skin, Left Side, Top........ Figure 4/(Sheet 7).
85330106................................ Skin, Left Side, Bottom..... Figure 4/(Sheet 14).
85330105................................ Skin, Left Side............. Figure 4/(Sheet 15).
85330101................................ Skin, Left Side, Bottom..... Figure 4/(Sheet 16).
85330033................................ Skin, Bottom................ Figure 4/(Sheet 17).
85330032................................ Skin, Right Side, Lower..... Figure 4/(Sheet 18).
85330032................................ Skin, Right Side, Lower with Figure 4/(Sheet 19).
Service Door.
85330031................................ Skin, Left Side, Lower...... Figure 4/(Sheet 20).
85332750................................ Skin, Bottom, Center........ Figure 4/(Sheet 25).
85332750................................ Skin, Bottom, Center........ Figure 4/(Sheet 26).
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Repair
(g) If any disbonding is found during the resonance frequency
inspection required by paragraph (f) of this AD: Before further
flight, repair per a method approved by the Manager, New York ACO;
or TCCA (or its delegated agent).
Limitation on Future Inspections
(h) As of the effective date of this AD, no person may use PSM
1-83-7A, Revision 6, dated January 30, 2001, to inspect for
disbonding of fuselage skin panels on any airplane having any serial
number 202 through 298 inclusive.
Alternative Methods of Compliance (AMOCs)
(i) The Manager, New York ACO, has the authority to approve
AMOCs for this AD, if an AMOC is requested in accordance with the
procedures found in 14 CFR 39.19.
Related Information
(j) Canadian airworthiness directive CF-2002-08, dated January
25, 2002, also addresses the subject of this AD.
Issued in Renton, Washington, on August 25, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-20204 Filed 9-3-04; 8:45 am]
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