[Federal Register Volume 68, Number 64 (Thursday, April 3, 2003)]
[Rules and Regulations]
[Pages 16192-16195]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-7745]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-56-AD; Amendment 39-13099; AD 2003-07-03]
RIN 2120-AA64


Airworthiness Directives; Twin Commander Aircraft Corporation 
Models 690D, 695A, and 695B Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Twin Commander Aircraft Corporation (TCAC) Models 
690D, 695A, and 695B airplanes. This AD requires you to initially 
inspect and modify and repetitively inspect areas of the wing and 
fuselage structure for fatigue damage and modify or replace any damaged 
parts. This AD is the result of tests that show that the service life 
of certain airplane parts cannot be reached unless an inspection and 
modification program (with any necessary replacements or modifications 
if fatigue damage is found) is incorporated. The actions specified by 
this AD are intended to detect and correct fatigue damage in the wing 
and fuselage areas without reducing the service life of the airplane. 
Such undetected and uncorrected damage could result in structural 
failure with consequent loss of control of the airplane.

DATES: This AD becomes effective on May 16, 2003. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of May 16, 2003.

ADDRESSES: You may get the service information referenced in this AD 
from Twin Commander Aircraft Corporation, 19010 59th Drive NE., 
Arlington, Washington 98223-7832; telephone: (360) 435-9797; facsimile: 
(360) 435-1112. You may view this information at the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 2000-CE-56-AD, 901 Locust, Room 506, 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: Della Swartz, Aerospace Engineer, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4065; telephone: (425) 687-4246; facsimile: (425) 687-
4248.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

    The FAA has received results of fatigue testing of the wing and 
fuselage structure on Models 690D, 695A, and 695B airplanes. These 
results reveal that fatigue damage could occur prior to the published 
service lives.
    TCAC has developed an inspection and modification program to detect 
and correct fatigue damage in the wing and fuselage areas without 
reducing the service life of the airplanes.

What Is the Potential Impact if FAA Took No Action?

    Such fatigue damage, if not detected and corrected, could result in 
structural failure with consequent loss of control of the airplane.

Has FAA Taken Any Action to This Point?

    We issued a proposal to amend part 39 of the Federal Aviation 
Regulations (14 CFR part 39) to include an AD that would apply to 
certain TCAC Models 690D, 695A, and 695B airplanes. This proposal was 
published in the Federal Register as a notice of proposed rulemaking 
(NPRM) on December 3, 2002 (67 FR 71904). The NPRM proposed to require 
you to repetitively inspect areas of the wing and fuselage structure 
for fatigue damage and modify or replace any damaged parts.

[[Page 16193]]

Was the Public Invited To Comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. We did not receive any comments on the proposed rule 
or on our determination of the cost to the public.

FAA's Determination

What Is FAA's Final Determination on This Issue?

    After careful review of all available information related to the 
subject presented above, we have determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. We have determined that these minor 
corrections:

--Provide the intent that was proposed in the NPRM for correcting the 
unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD affects 108 airplanes in the U.S. 
registry.

What Is the Cost Impact of This AD on Owners/Operators of the Affected 
Airplanes?

    We estimate the following costs to do the inspection for TCAC 
Models 690D, 695A, and 695B airplanes:

------------------------------------------------------------------------
  Inspection only labor cost for       Total inspection cost on U.S.
          each airplane                          operators
------------------------------------------------------------------------
Minimum 270 workhours x $60 per    Minimum: $1,749,600.
 hour = $16,200.
Maximum 416 workhours x $60 each   Maximum: $2,695,680.
 hour = $24,960.
------------------------------------------------------------------------

    We estimate the following costs to do any necessary modifications 
that will be required based on the results of the inspection. We have 
no way of finding out the number of airplanes that may need 
modifications:

------------------------------------------------------------------------
              Costs                     Minimum             Maximum
------------------------------------------------------------------------
Labor Costs.....................  81 workhours x $60  2,790 workhours x
                                   per hour = $4,860.  $60 per hour =
                                                       $167,400.
Estimated Parts Cost............  $2,847............  $65,978.
Estimated Total Cost for Each     $7,707............  $233,378.
 Airplane.
Total Cost on U.S. Operators....  $832,356..........  $25,204,824.
------------------------------------------------------------------------

Compliance Time

Why Is the Initial Compliance Time Presented in Hours Time-in-Service 
(TIS) and Calendar Time?

    Normally, fatigue problems carry a compliance time based solely 
upon hours TIS, e.g., upon accumulating a certain amount of hours TIS. 
However, the number of airplanes that still need to have the initial 
actions of this AD accomplished compared to the number of authorized 
repair centers justifies a compliance time of both hours TIS and 
calendar time, whichever occurs first.
    TCAC estimates 125 airplanes worldwide (about 87 percent of the 
worldwide fleet) that still need to have the initial inspections 
accomplished. This 87 percent would amount to 94 of the 108 U.S.-
registered airplanes with only 7 authorized service centers accredited 
to do the work. The FAA has worked with TCAC in establishing a 
compliance table that categorizes the airplanes based upon the amount 
of hours TIS each airplane has accumulated.
    This will ensure that the service centers have adequate time to 
accomplish the actions required by this AD.

Regulatory Impact

Does This AD Impact Various Entities?

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    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

0
Accordingly, under 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

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. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2003-07-03 Twin Commander Aircraft Corporation: Amendment 39-13099; 
Docket No. 2000-CE-56-AD.

    (a) What airplanes are affected by this AD? This AD affects the 
following Twin Commander Aviation Corporation (TCAC) airplane models 
and serial numbers that are certificated in any category:

[[Page 16194]]



------------------------------------------------------------------------
               Model                             Serial Nos.
------------------------------------------------------------------------
690D..............................  15001 through 15036 and 15038
                                     through 15040.
-----------------------------------
695A..............................  96001 through 96062, 96065 through
                                     96068, 96070, 96071, 96073, 96074,
                                     96076, 96077, and 96079 through
                                     96084, 96086, 96087, and 96089
                                     through 96100.
-----------------------------------
695B..............................  96063, 96069, 96075, 96078, 96085,
                                     and 96204 through 96208.
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the airplanes identified in paragraph (a) of this AD must 
comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to detect and correct fatigue damage in the 
wing and fuselage areas without reducing the service life of the 
airplane. Such undetected and uncorrected damage could result in 
structural failure with consequent loss of control of the airplane.
    (d) What must I do to address this problem? To address this 
problem, you must initially inspect and modify the wing and fuselage 
areas (Part 1 Inspection/Modifications as identified in Twin 
Commander Aircraft Corporation Mandatory Service Bulletin No. 214, 
dated January 26, 2000) and repetitively inspect with necessary 
modification or replacement of damaged parts (Part 2 Recurrent 
Inspections as identified in Twin Commander Aircraft Corporation 
Mandatory Service Bulletin No. 214, dated January 26, 2000) in 
accordance with the following schedules:
    (1) Part 1 Initial Inspections/Modifications: Initially (unless 
already done) accomplish the Part 1 Inspections/Modifications at 
whichever compliance time in paragraph (d)(1)(i) or (d)(1)(ii) of 
this AD that occurs later:
    (i) the compliance times presented in Part 1 Table 1 of Twin 
Commander Aircraft Corporation Mandatory Service Bulletin No. 214, 
dated January 26, 2000; Twin Commander Aircraft Corporation Service 
Publications revision notice to Service Bulletin No. 214, Revision 
1, Release Date: April 19, 2000; and Twin Commander Aircraft 
Corporation Service Publications revision notice to Service Bulletin 
No. 214, Revision 2, Release Date: May 21, 2001; or
    (ii) the Table A compliance times presented on page 1 of the 
service information and replicated below:

------------------------------------------------------------------------
  Current airframe hours time-in-
           service (TIS)                   Initial compliance time
------------------------------------------------------------------------
(A) 0000 through 1,700............  Upon accumulating 2,700 hours TIS or
                                     within the next 36 months after May
                                     16, 2003 (the effective date of
                                     this AD), whichever occurs first.
-----------------------------------
(B) 1,701 through 2,500...........  Upon accumulating 3,400 hours TIS or
                                     within the next 36 months after May
                                     16, 2003 (the effective date of
                                     this AD), whichever occurs first.
-----------------------------------
(C) 2,501 through 3,000...........  Upon accumulating 3,800 hours TIS or
                                     within the next 36 months after May
                                     16, 2003 (the effective date of
                                     this AD), whichever occurs first.
-----------------------------------
(D) 3,001 through 5,000...........  Upon accumulating 5,500 hours TIS or
                                     within the next 30 months after May
                                     16, 2003 (the effective date of
                                     this AD), whichever occurs first.
-----------------------------------
(E) 5,001 through 6,000...........  Upon accumulating 6,400 hours TIS or
                                     within the next 24 months after May
                                     16, 2003 (the effective date of
                                     this AD), whichever occurs first.
-----------------------------------
(F) 6,001 through 7,500...........  Upon accumulating 7,800 hours TIS or
                                     within the next 18 months after May
                                     16, 2003 (the effective date of
                                     this AD), whichever occurs first.
-----------------------------------
(G) Over 7,500....................  Within the next 12 months after May
                                     16, 2003 (the effective date of
                                     this AD).
------------------------------------------------------------------------

    (2) Part 2 Recurring Inspections: Repetitively inspect as 
referenced in Part 2 Recurring Inspections on page 62 of Twin 
Commander Aircraft Corporation Mandatory Service Bulletin No. 214, 
dated January 26, 2000; Twin Commander Aircraft Corporation Service 
Publications revision notice to Service Bulletin No. 214, Revision 
1, Release Date: April 19, 2000; and Twin Commander Aircraft 
Corporation Service Publications revision notice to Service Bulletin 
No. 214, Revision 2, Release Date: May 21, 2001.
    (3) Mandatory Replacements and Modifications: If any damage is 
found during any inspection required by paragraphs (d), (d)(1), and 
(d)(2) of this AD, prior to further flight, replace or modify the 
part as specified in the following:
    (i) Twin Commander Aircraft Corporation Mandatory Service 
Bulletin No. 214, dated January 26, 2000;
    (ii) Twin Commander Aircraft Corporation Service Publications 
revision notice to Service Bulletin No. 214, Revision 1, Release 
Date: April 19, 2000; and
    (iii) Twin Commander Aircraft Corporation Service Publications 
revision notice to Service Bulletin No. 214, Revision 2, Release 
Date: May 21, 2001.
    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Seattle Aircraft Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Seattle ACO.

    Note: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 request approval for an alternative method of 
compliance in accordance with paragraph (e) of this AD. The request 
should include an assessment of the effect of the modification, 
alteration, or repair on the unsafe condition addressed by this AD; 
and, if you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? Contact Della Swartz, Aerospace 
Engineer, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW, Renton, Washington 98055-4065; telephone: (425) 687-
4246; facsimile: (425) 687-4248.
    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.

[[Page 16195]]

    (h) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Twin Commander Aircraft Corporation Mandatory Service Bulletin 
No. 214, dated January 26, 2000; Twin Commander Aircraft Corporation 
Service Bulletin No. 214, Revision 1, Release Date: April 19, 2000; 
and Twin Commander Aircraft Corporation Service Bulletin No. 214, 
Revision 2, Release Date: May 21, 2001. The Director of the Federal 
Register approved this incorporation by reference under 5 U.S.C. 
552(a) and 1 CFR part 51. You may get copies from Twin Commander 
Aircraft Corporation, 19010 59th Drive N.E., Arlington, Washington 
98223-7832; telephone: (360) 435-9797; facsimile: (360) 435-1112. 
You may view copies at the FAA, Central Region, Office of the 
Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.
    (i) When does this amendment become effective? This amendment 
becomes effective on May 16, 2003.

    Issued in Kansas City, MO, on March 25, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-7745 Filed 4-2-03; 8:45 am]
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