Document ID: FAA-2008-0444-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Viking Air Limited Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-3 Airplanes
Posted Date: 2008-04-18T04:00Z

[Federal Register: April 18, 2008 (Volume 73, Number 76)]
[Proposed Rules]               
[Page 21074-21076]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18ap08-14]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0444; Directorate Identifier 2008-CE-024-AD]
RIN 2120-AA64

 
Airworthiness Directives; Viking Air Limited Models DHC-2 Mk. I, 
DHC-2 Mk. II, and DHC-3 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify and correct an unsafe condition on an aviation product. The 
MCAI describes the unsafe condition as:

    A complete loss of both ignition systems occurred on a DHC-3 
Otter when the lock wire hole in the ignition connector plug on the 
firewall broke out, allowing the plug to vibrate loose. A 
maintenance safety feature grounds out both magneto systems through 
a spring-loaded safety pin incorporated into the Cannon plug. The 
DHC-2 system is similar in design.
    Subsequent to the issuance of AD CF-2001-36 a complete loss of 
both ignition systems occurred on a DHC-2 Beaver resulting in engine 
failure and subsequent forced approach and landing. Investigation by 
the Transportation Safety Board determined the internal failure of 
the magneto firewall connector resulted in both magneto ``P'' leads 
shorting to ground. A maintenance ``safety'' feature through a 
spring-loaded safety pin incorporated in the firewall connector on 
many DHC-2 aircraft grounds out both magneto systems when the 
connector is disconnected. This connector type is readily identified 
when disconnected by the existence of three internal pins on the 
firewall and magneto harness side, one of which is shorted directly 
to ground.

The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by May 19, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Fabio Buttitta, Aerospace Engineer, 
FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 
410, Westbury, New York 11590; telephone: (516) 228-7303; fax: (516) 
794-5531.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0444; 
Directorate Identifier 2008-CE-024-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://
regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On October 12, 2004, we issued AD 2004-21-06, Amendment 39-13827 
(69 FR 61758, October 21, 2004). That AD required actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2004-21-06, the manufacturer has developed a 
modification kit to replace the magneto firewall connector with parts 
of improved design.
    Transport Canada, which is the aviation authority for Canada, has 
issued AD No. CF-2001-36R1, dated January 21, 2008, and AD No. CF-2001-
37R, dated January 21, 2008 (referred to after this as ``the MCAI''), 
to correct an unsafe condition for the specified products. The MCAI 
states:

    A complete loss of both ignition systems occurred on a DHC-3 
Otter when the lock wire hole in the ignition connector plug on the 
firewall broke out, allowing the plug to vibrate loose. A 
maintenance safety feature grounds out both magneto systems through 
a spring-loaded safety pin incorporated into the Cannon plug. The 
DHC-2 system is similar in design.
    Subsequent to the issuance of AD CF-2001-36 a complete loss of 
both ignition systems occurred on a DHC-2 Beaver resulting in engine 
failure and subsequent forced approach and landing. Investigation by 
the Transportation Safety Board determined the internal failure of 
the magneto firewall connector resulted in both magneto ``P'' leads 
shorting to ground. A maintenance ``safety'' feature through a 
spring-loaded safety pin incorporated in the firewall connector on 
many DHC-2 aircraft ground out both magneto systems when the

[[Page 21075]]

connector is disconnected. This connector type is readily identified 
when disconnected by the existence of three internal pins on the 
firewall and magneto harness side, one of which is shorted directly 
to ground.
    These connectors are no longer in production.
    Since no effective Instructions for Continued Airworthiness 
exist to ensure the safety feature of these connectors will operate 
correctly when disconnected, or will ensure the internal integrity 
of the connector while in service, this directive is revised to 
mandate replacement of connectors with a different design.
    Viking Air Limited has developed SB V2/0001 to provide for the 
installation of a replacement connector, similar in design to 
magneto systems in service today. This modification incorporates a 
``straight through'' type connector, ensuring magneto circuit 
integrity should the connection open.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Viking Air Limited has issued the following service bulletins:
     Viking DHC-2 Beaver Service Bulletin Number V2/0001, dated 
June 27, 2007; and
     Viking DHC-3 Otter Service Bulletin Number V3/0001, dated 
June 27, 2007.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are proposing this AD because 
we evaluated all information and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.

Differences Between This Proposed AD and the MCAI or Service 
Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    We estimated that this proposed AD will affect 159 products of U.S. 
registry. We also estimate that it would take about 10 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $80 per work-hour. Required parts would cost 
about $881 per product.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $267,279, or $1,681 per product.

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 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 this 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 and placed it in the AD docket.

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 removing Amendment 39-13827 (69 FR 
61758; October 21, 2004), and adding the following new AD:

Viking Air Limited: Docket No. FAA-2008-0444; Directorate Identifier 
2008-CE-024-AD.

Comments Due Date

    (a) We must receive comments by May 19, 2008.

Affected ADs

    (b) This AD supersedes AD 2004-21-06, Amendment 39-13827.

Applicability

    (c) This AD applies to the following model and serial number 
airplanes certificated in any category:

------------------------------------------------------------------------
                 Model                             Serial No.
------------------------------------------------------------------------
DHC-2 Mk. I...........................  All.
DHC-2 Mk. II..........................  All.
DHC-3.................................  All serial numbers with piston
                                         engines.
------------------------------------------------------------------------

Subject

    (d) Air Transport Association of America (ATA) Code 26: Fire 
Protection.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    A complete loss of both ignition systems occurred on a DHC-3 
Otter when the lock wire hole in the ignition connector plug on the 
firewall broke out, allowing the plug to vibrate loose. A 
maintenance safety feature grounds out both magneto systems through 
a spring-loaded safety pin incorporated into the Cannon plug. The 
DHC-2 system is similar in design.
    Subsequent to the issuance of AD CF-2001-36 a complete loss of 
both ignition systems occurred on a DHC-2 Beaver resulting in engine 
failure and subsequent forced approach and landing. Investigation by 
the Transportation Safety Board

[[Page 21076]]

determined the internal failure of the magneto firewall connector 
resulted in both magneto ``P'' leads shorting to ground. A 
maintenance ``safety'' feature through a spring-loaded safety pin 
incorporated in the firewall connector on many DHC-2 aircraft ground 
out both magneto systems when the connector is disconnected. This 
connector type is readily identified when disconnected by the 
existence of three internal pins on the firewall and magneto harness 
side, one of which is shorted directly to ground.
    These connectors are no longer in production.
    Since no effective Instructions for Continued Airworthiness 
exist to ensure the safety feature of these connectors will operate 
correctly when disconnected, or will ensure the internal integrity 
of the connector while in service, this directive is revised to 
mandate replacement of connectors with a different design.
    Viking Air Limited has developed SB V2/0001 to provide for the 
installation of a replacement connector, similar in design to 
magneto systems in service today. This modification incorporates a 
``straight through'' type connector, ensuring magneto circuit 
integrity should the connection open.

Actions and Compliance

    (f) Inspect the connector plugs on the fore side of the firewall 
for security and the connector plug lockwire to ensure it is intact 
and the holes in the plugs are not broken out or cracked. Initially 
inspect within the next 100 hours time-in-service (TIS) after 
December 6, 2004 (the compliance date retained from AD 2004-21-06). 
Repetitively inspect thereafter at intervals not to exceed 100 hours 
TIS until the modification required in paragraph (h) of this AD is 
done. Do the inspections following deHavilland Beaver Alert Service 
Bulletin Number A2/53, Revision B, dated May 28, 2004; and 
deHavilland Otter Alert Service Bulletin Number A3/53, Revision B, 
dated May 28, 2004, as applicable.
    (g) During any inspection required in paragraph (f) of this AD, 
if the lockwire holes or the lockwire is found damaged, install 
Modification Kit Number C2VMK0001-1 or Modification Kit Number 
C3VMK0001-1, as applicable. Install the modification kit before 
further flight following the Accomplishment Instructions in Viking 
DHC-2 Beaver Service Bulletin Number V2/0001, dated June 27, 2007; 
and Viking DHC-3 Otter Service Bulletin Number V3/0001, dated June 
27, 2007, as applicable. Installing the modification kit terminates 
the repetitive inspections required in paragraph (f) of this AD.
    (h) Unless already done, replace the magneto firewall connector 
by installing Modification Kit Number C2VMK0001-1 or Modification 
Kit Number C3VMK0001-1, as applicable. Install the modification kit 
within the next 6 months after the effective date of this AD 
following the Accomplishment Instructions in Viking DHC-2 Beaver 
Service Bulletin Number V2/0001, dated June 27, 2007; and Viking 
DHC-3 Otter Service Bulletin Number V3/0001, dated June 27, 2007, as 
applicable. Installing the modification kit terminates the 
repetitive inspections required in paragraph (f) of this AD.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: AD 2004-21-06 required incorporating repetitive 
inspections of the connector plugs and the connector plug lockwire 
on the fore side of the firewall into the maintenance program while 
the MCAI required incorporating Temporary Revision No. 14, dated 
August 24, 2001, into the applicable maintenance manual in order to 
incorporate the repetitive inspections into the maintenance program.

Other FAA AD Provisions

    (i) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (ACO), FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. Send information to ATTN: Fabio Buttitta, Aerospace 
Engineer, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, 
Westbury, New York 11590; telephone: (516) 228-7303; fax: (516) 794-
5531. Before using any approved AMOC on any airplane to which the 
AMOC applies, notify your appropriate principal inspector (PI) in 
the FAA Flight Standards District Office (FSDO), or lacking a PI, 
your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (j) Refer to MCAI Transport Canada AD No. CF-2001-36R1, dated 
January 21, 2008; and AD No. CF-2001-37R, dated January 21, 2008; 
and Viking Air Limited DHC-2 Beaver Service Bulletin Number V2/0001, 
dated June 27, 2007; and Viking Air Limited DHC-3 Otter Service 
Bulletin Number V3/0001, dated June 27, 2007; for related 
information.

    Issued in Kansas City, Missouri, on April 11, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-8365 Filed 4-17-08; 8:45 am]

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