Airworthiness Directives; Viking Air Limited Models DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 Airplanes, 16782-16784 [E8-6469]

Download as PDF 16782 Federal Register / Vol. 73, No. 62 / Monday, March 31, 2008 / Proposed Rules appropriate PMI in the FAA Flight Standards District Office (FSDO), or lacking a PMI, 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. DOCKET NO. FAA–2008–0367 INSPECTION REPORT [Report only if you find level 3 corrosion] 1. Operator: 2. Telephone: 3. Airplane Model Number: 4. Airplane Serial Number: 5. Airplane Tail Number: 6. Date of Inspection: 7. Corrosion Task: 8. Description & Specific Location of Findings: 9. Additional Comments of Owner/Operator: Send to: Viking Air Limited VP Engineering 9574 Hampden Road Sidney, British Columbia, Canada V8L 5V5 Telephone: 250.656.7227 Fax: 250.656.9702 Figure 1. Related Information DEPARTMENT OF TRANSPORTATION (h) Refer to MCAI Transport Canada AD No. CF–94–12R1, dated April 13, 1999; and Transport Canada AD No. CF–99–11, dated May 28, 1999; and DHC–6 Twin Otter (Series 100/200/300) Corrosion Prevention and Control Manual PSM 1–6–5, Revision 3, dated January 15, 2007; and the temporary revisions listed in Table 1—Viking Temporary Revisions, of this AD, for related information. jlentini on PROD1PC65 with PROPOSALS David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–6468 Filed 3–28–08; 8:45 am] BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0368; Directorate Identifier 2008–CE–007–AD] RIN 2120–AA64 Airworthiness Directives; Viking Air Limited Models DHC–6–1, DHC–6–100, DHC–6–200, and DHC–6–300 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing VerDate Aug<31>2005 16:12 Mar 28, 2008 Jkt 214001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 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: There have been reports of inter-rivet cracking on several wing front spar adapter assemblies (P/N C6WM1027–1) on the horizontal and vertical flanges. It was determined that the cracking was caused by stress corrosion in the short transverse grain initiated by local riveting induced stresses. 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 April 30, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. E:\FR\FM\31MRP1.SGM 31MRP1 Federal Register / Vol. 73, No. 62 / Monday, March 31, 2008 / Proposed Rules • 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. There have been reports of inter-rivet cracking on several wing front spar adapter assemblies (P/N C6WM1027–1) on the horizontal and vertical flanges. It was determined that the cracking was caused by stress corrosion in the short transverse grain initiated by local riveting induced stresses. This directive mandates modification and inspection of the wing front spar adapter fitting and replacement of cracked fittings. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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: Pong Lee, Aerospace Engineer, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone: (516) 228–7324; fax: (516) 794–5531. SUPPLEMENTARY INFORMATION: Relevant Service Information Viking Air Limited has issued the following DHC–6 Twin Otter Service Bulletins: • No. V6/540, dated October 1, 2007; • No. V6/541, dated October 1, 2007; and • No. V6/542, dated October 1, 2007. R.W. Martin, Inc. has issued Service Bulletin No. 00160/2, Revision A, dated November 15, 2007. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. jlentini on PROD1PC65 with PROPOSALS 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–2008–0368; Directorate Identifier 2008–CE–007–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 https:// www.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 Transport Canada, which is the aviation authority for Canada, has issued AD No. CF–2007–31, dated December 17, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: VerDate Aug<31>2005 16:12 Mar 28, 2008 Jkt 214001 You may obtain further information by examining the MCAI in the AD docket. 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 Based on the service information, we estimate that this proposed AD would PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 16783 affect about 157 products of U.S. registry. We also estimate that it would take about 18 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $226,080 or $1,440 per product. In addition, we estimate that any necessary follow-on actions would take about 200 work-hours and require parts costing $3,696 for a cost of $19,696 per product. 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 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 E:\FR\FM\31MRP1.SGM 31MRP1 16784 Federal Register / Vol. 73, No. 62 / Monday, March 31, 2008 / Proposed Rules 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Viking Air Limited: Docket No. FAA–2008– 0368; Directorate Identifier 2008–CE– 007–AD. Comments Due Date (a) We must receive comments by April 30, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Models DHC–6–1, DHC–6–100, DHC–6–200, and DHC–6–300 airplanes, all serial numbers, that are: (1) Equipped with wing boxes, part numbers (P/Ns) C6W1002–1, C6W1002–3, WR6–1002–59, or WR6–1002–61, that incorporate a P/N C6WM1027–1 front spar adapter assembly with 10 or more years of service; and (2) Certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 57: Wings. jlentini on PROD1PC65 with PROPOSALS Reason (e) The mandatory continuing airworthiness information (MCAI) states: There have been reports of inter-rivet cracking on several wing front spar adapter assemblies (P/N C6WM1027–1) on the horizontal and vertical flanges. It was determined that the cracking was caused by stress corrosion in the short transverse grain initiated by local riveting induced stresses. This directive mandates modification and inspection of the wing front spar adapter fitting and replacement of cracked fittings. Actions and Compliance (f) Unless already done, do the following actions: (1) Within the next 180 days after the effective date of this AD, install inspection holes in the left-hand (LH) and right-hand (RH) lower wing skins following Viking DHC–6 Twin Otter Service Bulletin Number V6/541, dated October 1, 2007. (2) Before further flight after installing the inspection holes required in paragraph (f)(1) VerDate Aug<31>2005 16:12 Mar 28, 2008 Jkt 214001 of this AD, inspect the LH and RH front spar adapter assemblies for cracks. For wing box P/Ns C6W1002–1 and C6W1002–3, inspect following Viking DHC–6 Twin Otter Service Bulletin Number V6/540, dated October 1, 2007. For wing box P/Ns WR6–1002–59 and WR6–1002–61, inspect following R.W. Martin, Inc. Service Bulletin No. 00160/2, Revision A, dated November 15, 2007. Repetitively inspect all affected wing box P/Ns thereafter at intervals not to exceed 1,200 hours time-in-service or 12 months, whichever occurs first, until the replacement required in paragraph (f)(3) of this AD is done. (3) Before further flight after doing any inspection required in paragraph (f)(2) of this AD where cracks are found, replace the cracked front spar adapter assembly with a front spar adapter assembly, P/N C6WM1027–3. Do the replacement following Viking DHC–6 Twin Otter Service Bulletin Number V6/542, dated October 1, 2007. This replacement terminates the repetitive inspections required in paragraph (f)(2) of this AD for the replaced front spar adapter assembly. (4) As a terminating action for the repetitive inspections required in paragraph (f)(2) of this AD, at any time after the initial inspection required in paragraph (f)(2) of this AD, you may replace P/N C6WM1027–1 with P/N C6WM1027–3. 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. FAA AD Differences this proposed AD and placed it in the AD docket. BILLING CODE 4910–13–P Note: This AD differs from the MCAI and/ or service information as follows: (1) MCAI Transport Canada AD No. CF–2007–31, dated December 17, 2007, requires incorporating task C57–10–18 of the DHC–6 Corrosion Prevention and Control Manual (CPCM), PSM 1–6–5, within 90 days after the effective date of this AD. (2) We are not incorporating task C57–10– 18 of the DHC–6 CPCM, PSM 1–6–5, into this AD because we are currently examining Transport Canada AD No. CF–94–12R1, dated April 13, 1999; and AD No. CF–99–11, dated May 28, 1999. Transport Canada issued these ADs to incorporate a Corrosion Prevention and Control Program that identifies specific areas that must be inspected to ensure the structural integrity of the DHC–6 fleet. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, 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: Pong Lee, Aerospace Engineer, FAA, New York Aircraft Certification Office,1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone: (516) 228–7324; 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 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Related Information (h) Refer to MCAI Transport Canada AD No. CF–2007–31, dated December 17, 2007; Viking DHC–6 Twin Otter Service Bulletins No. V6/540, dated October 1, 2007; No. V6/ 541, dated October 1, 2007; and No. V6/542, dated October 1, 2007; and R.W. Martin, Inc. Service Bulletin No. 00160/2, Revision A, dated November 15, 2007, for related information. Issued in Kansas City, Missouri, on March 8, 2008. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–6469 Filed 3–28–08; 8:45 am] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0365; Directorate Identifier 2007–NM–274–AD] RIN 2120–AA64 Airworthiness Directives; Dassault ` Model Mystere-Falcon 900 and Falcon 900EX Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. 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: This Airworthiness Directive (AD) is issued following the discovery of a potential chafing between the feeder bundle and the right side partition wall separating the cabin from the lavatory at frames 22/23. This chafing may damage the feeder bundle and cause a sustained smoke-generating shortcircuit between the feeder and the partition E:\FR\FM\31MRP1.SGM 31MRP1

Agencies

[Federal Register Volume 73, Number 62 (Monday, March 31, 2008)]
[Proposed Rules]
[Pages 16782-16784]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-6469]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0368; Directorate Identifier 2008-CE-007-AD]
RIN 2120-AA64


Airworthiness Directives; Viking Air Limited Models DHC-6-1, DHC-
6-100, DHC-6-200, and DHC-6-300 Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. 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:

    There have been reports of inter-rivet cracking on several wing 
front spar adapter assemblies (P/N C6WM1027-1) on the horizontal and 
vertical flanges. It was determined that the cracking was caused by 
stress corrosion in the short transverse grain initiated by local 
riveting induced stresses.

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 April 30, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.

[[Page 16783]]

     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 https://
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: Pong Lee, Aerospace Engineer, FAA, New 
York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, 
Westbury, New York 11590; telephone: (516) 228-7324; 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-2008-0368; 
Directorate Identifier 2008-CE-007-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 https://
www.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

    Transport Canada, which is the aviation authority for Canada, has 
issued AD No. CF-2007-31, dated December 17, 2007 (referred to after 
this as ``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    There have been reports of inter-rivet cracking on several wing 
front spar adapter assemblies (P/N C6WM1027-1) on the horizontal and 
vertical flanges. It was determined that the cracking was caused by 
stress corrosion in the short transverse grain initiated by local 
riveting induced stresses. This directive mandates modification and 
inspection of the wing front spar adapter fitting and replacement of 
cracked fittings.

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

Relevant Service Information

    Viking Air Limited has issued the following DHC-6 Twin Otter 
Service Bulletins:
     No. V6/540, dated October 1, 2007;
     No. V6/541, dated October 1, 2007; and
     No. V6/542, dated October 1, 2007.
    R.W. Martin, Inc. has issued Service Bulletin No. 00160/2, Revision 
A, dated November 15, 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

    Based on the service information, we estimate that this proposed AD 
would affect about 157 products of U.S. registry. We also estimate that 
it would take about 18 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $226,080 or $1,440 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 200 work-hours and require parts costing $3,696 for a cost 
of $19,696 per product. 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 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

[[Page 16784]]

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 adding the following new AD:

Viking Air Limited: Docket No. FAA-2008-0368; Directorate Identifier 
2008-CE-007-AD.

Comments Due Date

    (a) We must receive comments by April 30, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Models DHC-6-1, DHC-6-100, DHC-6-200, and 
DHC-6-300 airplanes, all serial numbers, that are:
    (1) Equipped with wing boxes, part numbers (P/Ns) C6W1002-1, 
C6W1002-3, WR6-1002-59, or WR6-1002-61, that incorporate a P/N 
C6WM1027-1 front spar adapter assembly with 10 or more years of 
service; and
    (2) Certificated in any category.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    There have been reports of inter-rivet cracking on several wing 
front spar adapter assemblies (P/N C6WM1027-1) on the horizontal and 
vertical flanges. It was determined that the cracking was caused by 
stress corrosion in the short transverse grain initiated by local 
riveting induced stresses. This directive mandates modification and 
inspection of the wing front spar adapter fitting and replacement of 
cracked fittings.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Within the next 180 days after the effective date of this 
AD, install inspection holes in the left-hand (LH) and right-hand 
(RH) lower wing skins following Viking DHC-6 Twin Otter Service 
Bulletin Number V6/541, dated October 1, 2007.
    (2) Before further flight after installing the inspection holes 
required in paragraph (f)(1) of this AD, inspect the LH and RH front 
spar adapter assemblies for cracks. For wing box P/Ns C6W1002-1 and 
C6W1002-3, inspect following Viking DHC-6 Twin Otter Service 
Bulletin Number V6/540, dated October 1, 2007. For wing box P/Ns 
WR6-1002-59 and WR6-1002-61, inspect following R.W. Martin, Inc. 
Service Bulletin No. 00160/2, Revision A, dated November 15, 2007. 
Repetitively inspect all affected wing box P/Ns thereafter at 
intervals not to exceed 1,200 hours time-in-service or 12 months, 
whichever occurs first, until the replacement required in paragraph 
(f)(3) of this AD is done.
    (3) Before further flight after doing any inspection required in 
paragraph (f)(2) of this AD where cracks are found, replace the 
cracked front spar adapter assembly with a front spar adapter 
assembly, P/N C6WM1027-3. Do the replacement following Viking DHC-6 
Twin Otter Service Bulletin Number V6/542, dated October 1, 2007. 
This replacement terminates the repetitive inspections required in 
paragraph (f)(2) of this AD for the replaced front spar adapter 
assembly.
    (4) As a terminating action for the repetitive inspections 
required in paragraph (f)(2) of this AD, at any time after the 
initial inspection required in paragraph (f)(2) of this AD, you may 
replace P/N C6WM1027-1 with P/N C6WM1027-3.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: (1) MCAI Transport Canada AD No. CF-2007-31, dated 
December 17, 2007, requires incorporating task C57-10-18 of the DHC-
6 Corrosion Prevention and Control Manual (CPCM), PSM 1-6-5, within 
90 days after the effective date of this AD.
    (2) We are not incorporating task C57-10-18 of the DHC-6 CPCM, 
PSM 1-6-5, into this AD because we are currently examining Transport 
Canada AD No. CF-94-12R1, dated April 13, 1999; and AD No. CF-99-11, 
dated May 28, 1999. Transport Canada issued these ADs to incorporate 
a Corrosion Prevention and Control Program that identifies specific 
areas that must be inspected to ensure the structural integrity of 
the DHC-6 fleet.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office, 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: Pong Lee, Aerospace 
Engineer, FAA, New York Aircraft Certification Office,1600 Stewart 
Avenue, Suite 410, Westbury, New York 11590; telephone: (516) 228-
7324; 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

    (h) Refer to MCAI Transport Canada AD No. CF-2007-31, dated 
December 17, 2007; Viking DHC-6 Twin Otter Service Bulletins No. V6/
540, dated October 1, 2007; No. V6/541, dated October 1, 2007; and 
No. V6/542, dated October 1, 2007; and R.W. Martin, Inc. Service 
Bulletin No. 00160/2, Revision A, dated November 15, 2007, for 
related information.

    Issued in Kansas City, Missouri, on March 8, 2008.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-6469 Filed 3-28-08; 8:45 am]
BILLING CODE 4910-13-P

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