Airworthiness Directives; Bombardier Model DHC-8-311 Airplanes

[Federal Register Volume 69, Number 172 (Tuesday, September 7, 2004)]
[Rules and Regulations]
[Pages 53999-54000]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-20204]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 69, No. 172 / Tuesday, September 7, 2004 / 
Rules and Regulations

[[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.

-----------------------------------------------------------------------

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, [email protected].

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
----------------------------------------------------------------------------------------------------------------
           Engineering drawing               Skin panel description             PSM 1-83-7A figure sheet
----------------------------------------------------------------------------------------------------------------
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).
----------------------------------------------------------------------------------------------------------------

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]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:02:15.503708+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

1d1589475eccb39b2b175d061e89b573b82b62ae2ed46c9812ae44b3606265b1

Text SHA-256

5ac23006edd46228c8339fcd097a42885d366c4993c97d19e162e71925c5d88a