[Federal Register Volume 70, Number 127 (Tuesday, July 5, 2005)]
[Rules and Regulations]
[Pages 38575-38578]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-12837]


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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..........
----------------------------------------------------------------------------------------------------------------

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