[Federal Register Volume 69, Number 130 (Thursday, July 8, 2004)]
[Proposed Rules]
[Pages 41213-41215]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-15515]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18563; Directorate Identifier 2002-NM-98-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-311 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Bombardier Model DHC-8-311 airplanes. This proposed AD 
would 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. This 
proposed 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 proposing 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: We must receive comments on this proposed AD by August 9, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://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.
    You may 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: 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.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

    The FAA has implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, new AD actions are posted on DMS 
and assigned a docket number. We track each action and assign a 
corresponding directorate identifier. The DMS AD docket number is in 
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane 
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier 
(``Old Docket Number'') as a cross-reference for searching purposes.

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-18563; 
Directorate Identifier

[[Page 41214]]

2002-NM-98-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 http://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 may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the Docket

    You may examine the AD docket 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-8-311 airplanes. TCCA advises that several 
fuselage skin panels were inadvertently omitted from the list of those 
to be inspected in Maintenance Program Support Manual (PSM) 1-83-7A, 
Revision 6, dated January 30, 2001. Though PSM 1-83-7A, Revision 7, 
dated August 15, 2001, has been issued, the omission of the subject 
fuselage skin panels from Revision 6 could result in the subject 
fuselage skin panels remaining uninspected until the next bonding 
integrity inspection. The repetitive interval for those inspections is 
3 years. Disbonding of the uninspected skin panels could occur in the 
interval between inspections. This condition, if not corrected, could 
reduce the load-carrying capacity of the skin panels and result in 
reduced structural integrity of the airplane.
    TCCA issued Canadian airworthiness directive CF-2002-08, dated 
January 25, 2002, to ensure the continued airworthiness of these 
airplanes in Canada.

FAA's Determination and Requirements of the Proposed AD

    This airplane model is manufactured in Canada and is 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 AD action is 
necessary for products of this type design that are certificated for 
operation in the United States. Therefore, we are proposing this AD, 
which would require you to review airplane maintenance records to 
determine if you did the most recent bonding integrity inspection 
according to PSM 1-83-7A, Revision 6. If you did the most recent 
bonding integrity inspection according to PSM 1-83-7A, Revision 6 (or 
if you can't conclusively determine what revision of the PSM you used), 
the proposed AD would require you to do a resonance frequency 
inspection for disbonding of the skin panels and repair if necessary. 
You must do the inspection for disbonding according to a method that 
either we or TCCA (or its delegated agent) approve. We approve PSM 1-
83-7A, Revision 7, as one method for accomplishing the inspection for 
disbonding. You must do any necessary repairs according to a method 
that we or TCCA (or its delegated agent) approve. This proposed AD 
would also prohibit you from using PSM 1-83-7A, Revision 6, for 
inspections for disbonding of fuselage skin panels performed after the 
effective date of the AD.

Costs of Compliance

    This proposed AD would affect about 8 airplanes of U.S. registry. 
The proposed records review would 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 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-2004-
18563; Directorate Identifier 2002-NM-98-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by August 9, 2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model DHC-8-311 airplanes, serial numbers 
202 through 298 inclusive, certificated in any category.

[[Page 41215]]

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      Figure 4/(Sheet 19).
                                            with 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 June 30, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-15515 Filed 7-7-04; 8:45 am]
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