[Federal Register Volume 63, Number 196 (Friday, October 9, 1998)]
[Rules and Regulations]
[Pages 54347-54349]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-26974]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-CE-54-AD; Amendment 39-10821; AD 98-08-25 R1]
RIN 2120-AA64


Airworthiness Directives; Twin Commander Aircraft Corporation 
500, 680, 690, and 695 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Direct final rule; request for comments.

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SUMMARY: This amendment revises Airworthiness Directive (AD) 98-08-25, 
which currently requires replacing the nose landing gear (NLG) drag 
link bolt with an approved heat-treated bolt that has the 
manufacturer's serial number, manufacture date, and the last three 
digits of the drawing number (055) on the bolt head on certain Twin 
Commander Aircraft Corporation (Twin Commander) 500, 680, 690, and 695 
series airplanes; and changing the bolt part number (P/N) to be 
installed on Models 690D and 695A from P/N ED10055 to P/N 750076-1. The 
FAA inadvertently transposed the serial numbers of the 4 affected Model 
695A airplanes. This AD retains the same actions of AD 98-08-25, and 
corrects the serial numbers of these 4 airplanes. Three of the four 
airplanes are not on the U.S. Register and the other one is already in 
compliance with the actions of AD 98-08-25. The actions specified in 
this AD are intended to continue to prevent the NLG from collapsing due 
to failure of a drag link bolt, which could result in loss of control 
of the airplane during landing operations.

DATES: Effective January 5, 1999.
    The incorporation by reference of certain publications listed in 
the regulations was previously approved by the Director of the Federal 
Register as of May 18, 1998 (63 FR 19387, April 20, 1998).
    Comments for inclusion in the Rules Docket must be received on or 
before December 14, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 96-CE-54-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.
    Service information that applies to this AD may be obtained from 
the Twin Commander Aircraft Corporation, 19010 59th Drive NE, 
Arlington, Washington 98223-7832; telephone: (360) 435-9797; facsimile: 
(360) 435-1112. This information may also be examined at the Federal 
Aviation Administration (FAA), Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 96-CE-54-AD, 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: Jeffrey Morfitt, Aerospace Engineer, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Ave. SW, Renton, 
Washington, 98055-4056; telephone: (206) 227-2595; facsimile: (206) 
227-1181.

SUPPLEMENTARY INFORMATION:

Discussion

    On April 9, 1998, the FAA issued AD 98-08-25, Amendment 39-10474 
(63 FR 19387, April 20, 1998), which applies to certain Twin Commander 
500, 680, 690, and 695 series airplanes. AD 98-08-25 currently requires 
replacing the NLG drag link bolt with an approved heat-treated bolt 
that has the manufacturer's serial number, manufacture date, and the 
last three digits of the drawing number (055) on the bolt head on all 
of the affected airplanes; and changing the bolt part number (P/N) to 
be installed from P/N ED10055 to P/N 750076-1, on Models 690D and 695A 
airplanes. Accomplishment of the actions of AD 98-08-25 are required in 
accordance with Twin Commander Service Bulletin 224, Revision C, dated 
July 25, 1996.
    The actions specified by AD 98-08-25 are intended to prevent the 
nose landing gear (NLG) from collapsing because of failure of a drag 
link bolt, which could result in loss of control of the airplane during 
landing operations.
    AD 98-08-25 was the result of the FAA's determination that a 
defective lot of drag link bolts used in the NLG was manufactured and 
distributed to the field.

Events Leading to the Issuance of This AD

    Since AD 98-08-25 became effective, the FAA has realized that it 
inadvertently transposed the serial numbers of the 4 affected Model 
695A airplanes. In particular, the AD currently contains Model 695A 
airplanes, serial numbers 69010, 69041, 69056, and 69061. The affected 
serial numbers should be 96010, 96041, 96056, and 96061.
    Three of the four airplanes are not on the U.S. Register and the 
other one is already in compliance with the actions of AD 98-08-25.

[[Page 54348]]

The FAA's Determination

    After examining all information related to the subject described 
above, the FAA has determined that additional AD action should be taken 
to:

--Correct the serial numbers of the Model 695A airplanes; and
--Continue to prevent the NLG from collapsing due to failure of a drag 
link bolt, which could result in loss of control of the airplane during 
landing operations.

Explanation of the Provisions of This AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Twin Commander 500, 680, 690, and 695 series 
airplanes of the same type design registered in the United States, the 
FAA is issuing an AD to revise AD 98-08-25. This AD retains the same 
actions of AD 98-08-25 for all of the affected airplanes, and corrects 
the serial numbers of the Model 695A airplanes.
    Accomplishment of the actions of this AD is still required in 
accordance with Twin Commander Service Bulletin 224, Revision C, dated 
July 25, 1996.

Cost Impact

    The FAA estimates that 54 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 1 workhour per 
airplane to accomplish these actions, and that the average labor rate 
is approximately $60 an hour. The manufacturer is providing parts and 
one hour labor free of charge. With this in mind, this AD imposes no 
cost impact upon the U.S. operators of the affected airplanes.
    The only difference between this AD and AD 98-08-25 is the revision 
to the serial numbers of the Model 695A airplanes. Of these 4 
airplanes, 3 are currently not on the U.S. registry and the other is 
already in compliance with the AD. Therefore, there is no cost impact 
of this AD over that already required by AD 98-08-25.

The Direct Final Rule Procedure

    The FAA anticipates that this regulation will not result in adverse 
or negative comment and therefore is issuing it as a direct final rule. 
Since the actions have already been incorporated on the one Model 695A 
airplane that is on the U.S. registry, this AD revision will impose no 
additional actions upon U.S. operators of the affected airplanes. In 
accordance with Sec. 11.17 of the Federal Aviation Regulations (14 CFR 
11.17) unless a written adverse or negative comment, or a written 
notice of intent to submit an adverse or negative comment, is received 
within the comment period, the regulation will become effective on the 
date specified above. After the close of the comment period, the FAA 
will publish a document in the Federal Register indicating that no 
adverse or negative comments were received and confirming the date on 
which the final rule will become effective. If the FAA does receive, 
within the comment period, a written adverse or negative comment, or 
written notice of intent to submit such a comment, a document 
withdrawing the direct final rule will be published in the Federal 
Register, and a notice of proposed rulemaking may be published with a 
new comment period.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and an opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
rule by submitting such written data, views, or arguments as they may 
desire. Communications shall identify the Rules Docket number and be 
submitted in triplicate to the address specified under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 96-CE-54-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    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.
    The FAA has determined that this regulation is noncontroversial and 
unlikely to result in adverse or negative comments. For reasons 
discussed in the preamble, I certify that this regulation (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 final 
evaluation has been prepared for this action and is contained in the 
Rules Docket. A copy of it may be obtained from 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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Airworthiness Directive 
(AD) 98-08-25, Amendment 39-10474 (63 FR 19387, April 20, 1998), and 
adding a new AD to read as follows:

98-08-25 R1  Twin Commander Aircraft Corporation: Amendment 39-
10821; Docket No. 96-CE-54-AD. Revises AD 98-08-25, Amendment 39-
10474, which superseded AD 96-12-08, Amendment 39-9650.

    Applicability: The following model and serial number airplanes, 
certificated in any category:

[[Page 54349]]



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               Models                            Serial Nos.
------------------------------------------------------------------------
500S...............................  3185, 3228, 3230, 3262, and 3291.
500U...............................  1765.
680F...............................  1195.
681................................  6027.
680V...............................  1677.
690................................  11035, 11053, 11068, and 11074.
690A...............................  11111, 11134, 11146, 11153, 11173,
                                      11177, 11205, 11215, 11237, 11249,
                                      11271, 11273, and 11282.
690B...............................  11360, 11382, 11409, 11424, 11451,
                                      11455, 11463, 11491, 11513, 11521,
                                      11535, 11536, 11539, and 11566.
690C...............................  11638, 11643, 11676, 11689, and
                                      11719.
690D...............................  15041.
695................................  95010, 95033, 95044, and 95066.
695A...............................  96010, 96041, 96056, and 96061.
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    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 request approval for an 
alternative method of compliance in accordance with paragraph (g) 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 the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated below, unless already 
accomplished:
    1. For all affected airplane models, except for Model 695A 
airplanes: Within 75 hours time-in-service (TIS) after May 18, 1998 
(the effective date of AD 98-08-25).
    2. For Model 695A airplanes: Within the next 75 hours TIS after 
the effective date of this AD.
    To prevent the nose landing gear (NLG) from collapsing due to 
failure of a drag link bolt, which could result in loss of control 
of the airplane during landing operations, accomplish the following:
    (a) For all airplane models, except for Models 690D and 695A, 
replace the NLG drag link bolt, part number (P/N) ED 10055, with a 
new bolt in accordance with the INSTRUCTIONS section of Twin 
Commander Service Bulletin (SB) 224, Revision C, dated July 25, 
1996.
    (b) For airplane Models 690D and 695A, replace the NLG drag link 
bolt (P/N ED 10055), with a new bolt (P/N 750076-1) in accordance 
with Twin Commander SB 224, Revision C, dated July 25, 1996.
    (c) The new replacement bolt must be marked with the 
manufacturer's serial number, the date of manufacture, and the last 
three digits of the drawing number, 055, on the bolt head for all 
but Models 690D and 695A. Models 690D and 695A bolts must be marked 
with the manufacturer's serial number, the date of manufacture, and 
the last three digits of the drawing number, 76-1, on the bolt head.

    Note 2: Although not required by this AD, FAA highly recommends 
that the removed bolt (P/N ED 10055) be returned to Twin Commander 
for Rockwell Hardness testing.

    (d) For all affected airplane models, except for Models 690D and 
695A airplanes, compliance with Twin Commander SB 224, Revision A, 
dated April 24, 1996; or Twin Commander SB 224, Revision C, dated 
July 25, 1996, fulfills the applicable requirements of this AD. For 
the affected Models 690 and 695A airplanes, compliance must be in 
accordance with Twin Commander SB 224, Revision C, dated July 25, 
1998.
    (e) As of the effective date of this AD, no person shall 
install, on any affected airplane, a NLG drag link bolt that does 
not have the manufacturer's serial number, manufacture date, and the 
last three digits of the drawing number as specified in paragraph 
(c) of this AD.
    (f) Special flight permits may be issued in accordance with 
Secs. 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.
    (g) An alternative method of compliance or adjustment of the 
compliance time that provides an equivalent level of safety may be 
approved by the Manager, Seattle Aircraft Certification Office, 1601 
Lind Ave. SW, 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 Aircraft 
Certification Office.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle Aircraft Certification Office.

    (h) The inspection and replacement required by this AD shall be 
done in accordance with Twin Commander Service Bulletin 224, 
Revision C, dated July 25, 1996. This incorporation by reference was 
previously approved by the Director of the Federal Register as of 
May 18, 1998 (63 FR 19387, April 20, 1998). Copies may be obtained 
from Twin Commander Aircraft Corporation, 19010 59th Drive NE, 
Arlington, Washington 98223-7832. Copies may be inspected at the 
FAA, Central Region, Office of the Regional 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.
    (i) This amendment revises AD 98-08-25, Amendment 39-10474, 
which superseded AD 96-12-08, Amendment No. 39-9650.
    (j) This amendment becomes effective on January 5, 1999.

    Issued in Kansas City, Missouri, on September 30, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-26974 Filed 10-8-98; 8:45 am]
BILLING CODE 4910-13-U