[Federal Register Volume 60, Number 121 (Friday, June 23, 1995)]
[Rules and Regulations]
[Pages 32583-32585]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-15013]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-CE-27-AD; Amendment 39-9283; AD 95-13-02]


Airworthiness Directives; Twin Commander Aircraft Corporation 
685, 690, and 695 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
[[Page 32584]] applies to certain Twin Commander Aircraft Corporation 
(Twin Commander) 685, 690, and 695 series airplanes. This action 
requires initially inspecting the vertical stabilizer for cracks, 
modifying any cracked vertical stabilizer, and, if not cracked, either 
repetitively inspecting or modifying the vertical stabilizer. Several 
reports of the vertical stabilizer cracking in different areas prompted 
this action. The actions specified by this AD are intended to prevent 
failure of the vertical stabilizer as a result of cracking, which, if 
not detected and corrected, could result in loss of control of the 
airplane.

DATES: Effective July 22, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 22, 1995.

ADDRESSES: Service information that applies to this AD may be obtained 
from the Twin Commander Aircraft Corporation, 19010 59th Drive, N.E., 
Arlington, Washington 98223. This information may also be examined at 
the Federal Aviation Administration (FAA), Central Region, Office of 
the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas 
City, Missouri 64106; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. David D. Swartz, Aerospace 
Engineer, FAA, Northwest Mountain Region, 1601 Lind Avenue S.W., 
Renton, Washington 98055-4056; telephone (206) 227-2624; facsimile 
(206) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that would apply 
to certain Twin Commander Models 685, 690, 690A, 690B, 690C, 690D, 695, 
and 695A airplanes was published in the Federal Register on February 1, 
1995 (60 FR 6045). The action proposed to require initially inspecting 
the vertical stabilizer for cracks, modifying any cracked vertical 
stabilizer, and, if not cracked, either repetitively inspecting or 
modifying the vertical stabilizer. Accomplishment of the proposed 
actions would be in accordance with Twin Commander Service Bulletin No. 
218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 
11, 1994, and September 23, 1994, respectively.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed rule or the FAA's determination of the cost to the public.
    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. The FAA has determined that these minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.
    The FAA estimates that 469 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 10 workhours per 
airplane to accomplish the required inspection, and that the average 
labor rate is approximately $60 an hour. Parts to accomplish the 
required inspection cost approximately $200 per airplane. Based on 
these figures, the total cost impact of this AD on U.S. operators is 
estimated to be $375,200. This figure does not take into account the 
cost of repetitive inspections or the cost of any modifications that 
may be needed based on the inspection results. The FAA has no way of 
determining how many vertical stabilizers may be cracked and need 
modification, or how many repetitive inspections each owner/operator 
may incur.
    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (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. A copy of the final evaluation prepared for this 
action is contained in the Rules Docket. A copy of it may be obtained 
by contacting the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.
Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new AD to read as follows:


95-13-02  Twin Commander Aircraft Corporation: Amendment 39-9283; 
Docket No. 94-CE-27-AD.

    Applicability: The following airplane models and serial numbers, 
certificated in any category, that do not have the vertical 
stabilizer modified in accordance with the ACCOMPLISHMENT 
INSTRUCTIONS: PART II--MODIFICATION section of Twin Commander 
Service Bulletin (SB) No. 218, dated May 19, 1994, including 
Revision Notices 1 and 2, dated July 11, 1994, and September 23, 
1994, respectively:

------------------------------------------------------------------------
               Model                            Serial numbers          
------------------------------------------------------------------------
685................................  12000 through 12066.               
690................................  11000 through 11079.               
690A...............................  11100 through 11344.               
690B...............................  11350 through 11566.               
690C...............................  11600 through 11735.               
690D...............................  15001 through 15042.               
695................................  95000 through 95084.               
695A...............................  96001 through 96100.               
------------------------------------------------------------------------

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must use the authority 
provided in paragraph (f) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition, or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required upon the accumulation of 2,000 hours time-
in-service (TIS) on a vertical stabilizer or within the next 50 
hours TIS after the effective date of this AD, whichever occurs 
later, unless already accomplished, and thereafter as indicated in 
the body of this AD. [[Page 32585]] 
    To prevent failure of the vertical stabilizer as a result of 
cracks, which, if not detected and corrected, could result in loss 
of control of the airplane, accomplish the following:
    (a) Inspect the vertical stabilizer for cracks in accordance 
with the ACCOMPLISHMENT INSTRUCTIONS: PART I--INSPECTION section of 
Twin Commander SB No. 218, dated May 19, 1994, including Revision 
Notices 1 and 2, dated July 11, 1994, and September 23, 1994, 
respectively.
    (b) If damage or cracks are found within the limits of Figures 1 
and 2 of the service information referenced above, prior to further 
flight, modify the vertical stabilizer in accordance with the 
ACCOMPLISHMENT INSTRUCTIONS: PART II--MODIFICATION section of Twin 
Commander SB No. 218, dated May 19, 1994, including Revision Notices 
1 and 2, dated July 11, 1994, and September 23, 1994, respectively.
    (c) If damage or cracks are found outside the limits referenced 
in Figures 1 and 2 of the service information referenced above or if 
cracks intersect, prior to further flight, replace the damaged parts 
with new parts in accordance with the applicable maintenance manual 
instructions. The requirements of this AD still apply when the 
damaged parts are replaced, unless the stabilizer is modified as 
specified in paragraph (b) of this AD.
    (d) If no cracks are found, accomplish one of the following:
    (1) Reinspect at intervals not to exceed 500 hours TIS, and 
modify any damaged or cracked vertical stabilizer as specified in 
paragraphs (b) and (c) of this AD; or
    (2) Prior to further flight, modify the vertical stabilizer in 
accordance with the ACCOMPLISHMENT INSTRUCTIONS: PART II--
MODIFICATION section of Twin Commander SB No. 218, dated May 19, 
1994, including Revision Notices 1 and 2, dated July 11, 1994, and 
September 23, 1994, respectively.
    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.
    (f) An alternative method of compliance or adjustment of the 
initial or repetitive compliance times that provides an equivalent 
level of safety may be approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA, Northwest Mountain Region, 1601 
Lind Avenue S.W., Renton, Washington 98055-4056. The request shall 
be forwarded through an appropriate FAA Maintenance Inspector, who 
may add comments and then send it to the Manager, Seattle ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

    (g) The inspections and modification required by this AD shall 
be done in accordance with Twin Commander Service Bulletin 218, 
dated May 19, 1994, including Revision Notices 1 and 2, dated July 
11, 1994, and September 23, 1994, respectively. This incorporation 
by reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Twin Commander Aircraft Corporation, 19003 59th Drive, 
NE., Arlington, Washington 98223. Copies may be inspected at the 
FAA, Central Region, Office of the Assistant Chief Counsel, Room 
1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (h) This amendment (39-9283) becomes effective on July 22, 1995.

    Issued in Kansas City, Missouri, on June 13, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-15013 Filed 6-22-95; 8:45 am]
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