AD 2007-12-13

[Federal Register Volume 72, Number 111 (Monday, June 11, 2007)]
[Rules and Regulations]
[Pages 31971-31973]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: E7-10981]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27193; Directorate Identifier 2007-CE-009-AD; 
Amendment 39-15091; AD 2007-12-13]
RIN 2120-AA64


Airworthiness Directives; Viking Air Limited (Type Certificate 
No. A-806 Previously Held by deHavilland Inc.) Models DHC-2 Mk. I, DHC-
2 Mk. II, and DHC-2 Mk. III Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. This AD results from mandatory 
continuing airworthiness information (MCAI) issued 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 report has been received of stress corrosion cracking 
occurring in the wing lift strut lower clevis fitting, part number 
C2W-1097A.

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective July 16, 2007.
    On July 16, 2007 the Director of the Federal Register approved the 
incorporation by reference of certain publications listed in this AD.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a> or in person at the Docket Management Facility, U.S. 
Department of Transportation, Docket Operations, M-30, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 
20590.

FOR FURTHER INFORMATION CONTACT: George J. Duckett, Aerospace Engineer, 
FAA, New York Aircraft Certification Office, 10 Fifth Street, Valley 
Stream, New York 11581; telephone: (516) 228-7325; fax: (516) 794-5531.

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. The streamlined process will allow us to adopt 
MCAI safety requirements in a more efficient manner and will reduce 
safety risks to the public. This process continues to follow all FAA AD 
issuance processes to meet legal, economic, Administrative Procedure 
Act, and Federal Register requirements. We also continue to meet our 
technical decision-making responsibilities to identify and correct 
unsafe conditions on U.S.-certificated products.
    This AD references the MCAI and related service information that we 
considered in forming the engineering basis to correct the unsafe 
condition. The AD contains text copied from the MCAI and for this 
reason might not follow our plain language principles.

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on March 22, 2007 (72 
FR 13448) and proposed to supersede AD 88-08-02, Amendment 39-5889. 
That NPRM proposed to correct an unsafe condition for the specified 
products. The MCAI states:

    A report has been received of stress corrosion cracking 
occurring in the wing lift strut lower clevis fitting, part number 
C2W-1097A.
    This AD revision is being issued to allow operators the option 
of continuing with the existing inspection intervals in accordance 
with CF-85-08R3 (Part A) or incorporating the improved alternate 
inspection method in accordance with Part B, to permit an increase 
in inspection intervals.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This 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 required 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 AD.

Costs of Compliance

    We estimate that this AD will affect 392 products of U.S. registry. 
We also estimate that it will take about 7 work-hours per product to 
comply with basic requirements of this AD. The average labor rate is 
$80 per work-hour. Based on these figures, we estimate the cost of this 
AD to the U.S. operators to be $219,520, or $560 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 7 work-hours and require parts costing $6,227 for each wing 
strut assembly, for a cost of $6,787 per wing strut assembly. We have 
no way of determining the number of products that may need these 
actions.

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 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;

[[Page 31972]]

    (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 and placed it in the AD Docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>; 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 the NPRM, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (telephone (800) 647-5227) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

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 removing Airworthiness Directive (AD) 
88-08-02, Amendment 39-5889, and adding the following new AD:

2007-12-13 Viking Air Limited (Type Certificate No. A-806 previously 
held by deHavilland Inc.): Amendment 39-15091; Docket No. FAA-2007-
27193; Directorate Identifier 2007-CE-009-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 16, 
2007.

Affected ADs

    (b) This AD supersedes AD 88-08-02, Amendment 39-5889.

Applicability

    (c) This AD applies to Models DHC-2 Mk. I, DHC-2 Mk. II, and 
DHC-2 Mk. III airplanes, all serial numbers, that:
    (1) Are certificated in any category; and
    (2) Are equipped with wing lift strut assemblies, part numbers 
(P/Ns) C2W1103, C2W1103A, C2W1104, or C2W1104A.

Subject

    (d) Air Transport Association of America (ATA) Code 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    A report has been received of stress corrosion cracking 
occurring in the wing lift strut lower clevis fitting, part number 
C2W-1097A.
    This AD revision is being issued to allow operators the option 
of continuing with the existing inspection intervals in accordance 
with CF-85-08R3 (Part A) or incorporating the improved alternate 
inspection method in accordance with Part B, to permit an increase 
in inspection intervals.

Restatement of Requirements of AD 88-08-02

    (f) For all Models DHC-2 Mk. I and DHC-2 Mk. III airplanes 
certificated in any category that are equipped with wing lift strut 
assemblies, P/Ns C2W1103, C2W1103A, C2W1104, or C2W1104A: Within the 
next 100 hours time-in-service (TIS) after May 11, 1988 (the 
effective date of AD 88-08-02) or one month after May 11, 1988 (the 
effective date of AD 88-08-02), whichever occurs first, and 
thereafter at intervals not to exceed 500 hours TIS or 12 calendar 
months, whichever occurs first, do the following:
    (1) Remove the wing lift strut assemblies, P/Ns C2W1103 or 
C2W1103A and C2W1104 or C2W1104A from the airplane and prepare the 
assemblies for inspection as described in the ``ACCOMPLISHMENT 
INSTRUCTIONS'' section of DeHavilland Service Bulletin (S/B) No. 2/
41, Revision A, dated August 14, 1987.
    (2) Conduct a dye penetrant inspection with a 10-power glass for 
cracks in the lugs of the lower attachment clevis fitting.
    (3) If cracks are found, before further flight, replace the 
complete wing lift strut assembly with a:
    (i) Wing lift strut assembly of the same part number that has 
had the lower clevis fitting inspected using the dye penetrant 
procedure and has been found free of cracks; or
    (ii) Wing lift strut assembly, P/N C2W1115-1 or P/N C2W1115-2, 
as appropriate.
    (4) If no cracks are found, before further flight, clean the 
lower clevis fitting and reinstall the wing lift strut assembly.
    (5) If wing strut assembly P/N C2W1115-1 or P/N C2W1115-2 is 
installed, the recurring inspection specified in paragraph (f) of 
this AD is no longer required.

New Requirements of This AD: Actions and Compliance

    (g) Unless already done, do either (1) or (2) of the following 
actions:
    (1) Inspection using fluorescent penetrant method: Perform the 
Accomplishment Instructions of Viking Air Ltd. Service Bulletin No. 
2/41, Revision C, dated June 23, 2006.
    (i) For airplanes previously affected by AD 88-08-02: Inspect 
the wing lift strut assemblies within the next 12 calendar months 
after the last inspection required by AD 88-08-02 or within the next 
30 days after July 16, 2007 (the effective date of this AD), 
whichever occurs later, and thereafter at intervals not to exceed 12 
calendar months.
    (ii) For airplanes not previously affected by AD 88-08-02: 
Inspect the wing lift strut assemblies within the next 100 hours 
time-in-service (TIS) after July 16, 2007 (the effective date of 
this AD) or within the next 12 calendar months after July 16, 2007 
(the effective date of this AD), whichever occurs first, and 
thereafter at intervals not to exceed 12 calendar months.
    (2) Inspection using eddy current method: Perform the 
Accomplishment Instructions of Viking Air Ltd. SB No. 2/55, dated 
June 23, 2006.
    (i) For airplanes previously affected by AD 88-08-02: Inspect 
the wing lift strut assemblies within the next 12 calendar months 
after the last inspection required by AD 88-08-02 or within the next 
30 days after July 16, 2007 (the effective date of this AD), 
whichever occurs later, and thereafter at intervals not to exceed 24 
calendar months.
    (ii) For airplanes not previously affected by AD 88-08-02: 
Inspect the wing lift strut assemblies within the next 100 hours TIS 
after July 16, 2007 (the effective date of this AD) or within the 
next 12 calendar months after July 16, 2007 (the effective date of 
this AD), whichever occurs first, and thereafter at intervals not to 
exceed 24 calendar months.
    (3) If cracks are found during any inspection required by either 
paragraph (g)(1) or (g)(2) of this AD, before further flight:
    (i) Replace the complete wing lift strut assembly with a wing 
lift strut assembly of the same part number that has had the lower 
clevis fitting inspected using either the fluorescent penetrant 
method specified in paragraph (g)(1) of this AD or the eddy current 
method specified in paragraph (g)(2) of this AD and is found free of 
cracks. After replacement, continue with the repetitive inspections 
specified in paragraphs (g)(1) and (g)(2) of this AD; or
    (ii) Replace the complete wing lift strut assembly with strut 
assembly C2W1115-1 or C2W1115-2, as appropriate. Installing wing 
strut assembly C2W1115-1 or C2W1115-2 as replacement parts 
terminates the repetitive inspections required in paragraphs (g)(1) 
and (g)(2) of this AD.
    (4) If no cracks are found during any inspection required in 
paragraphs (g)(1) or (g)(2) of this AD, before further flight, clean 
the lower clevis fitting and reinstall the wing strut assembly. 
After reinstallation, continue with the repetitive inspections 
specified in paragraphs (g)(1) and (g)(2) of this AD.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (h) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office, FAA, if requested using the 
procedures found in 14 CFR 39.19. Send information to ATTN: George 
J. Duckett, Aerospace Engineer, 10 Fifth Street, Valley Stream, New 
York 11581; telephone: (516) 228-7325; fax (516) 794-5531, has the

[[Page 31973]]

authority to approve AMOCs for this AD. 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) AMOCs approved for AD 88-08-02 are not approved for this AD.
    (3) 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.
    (4) 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

    (i) Refer to MCAI Transport Canada AD CR-1985-08R4, dated 
September 28, 2006; Viking Service Bulletin No. 2/41, Revision 
``C'', dated June 23, 2006; and Viking Service Bulletin No. 2/55, 
dated June 23, 2006; for related information.

Material Incorporated by Reference

    (j) You must use Viking Service Bulletin DHC-2 MK I, MK II and 
MK III Turbo Beaver Service Bulletin No. 2/41, Revision C, dated 
June 23, 2006; or Viking DHC-2 Beaver Service Bulletin No. 2/55, 
dated June 23, 2006, to do the actions required by this AD, unless 
the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Viking Air Limited, 9584 Hampden Rd., Sidney, BC, Canada, V8L 5V5; 
telephone: (250) 656-7227.
    (3) You may review copies at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 
64106; or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Kansas City, Missouri, on May 31, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-10981 Filed 6-8-07; 8:45 am]
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