[Federal Register Volume 61, Number 246 (Friday, December 20, 1996)]
[Rules and Regulations]
[Pages 67195-67197]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-31114]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-158-AD; Amendment 39-9845; AD 96-25-03]
RIN 2120-AA64


Airworthiness Directives; Raytheon (Beech) Model 400A, 400T 
(Military T-1A), and 400T (Military TX) Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

[[Page 67196]]

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Raytheon (Beech) Model 400A and 400T series 
airplanes, that currently requires an inspection of certain flap roller 
retention components to detect discrepant or missing parts; replacement 
of those parts; and installation of new washers on the roller attach 
bolts. This amendment requires the replacement of certain previously-
installed washers with new and stronger washers. This amendment also 
expands the applicability of the rule to include additional airplanes. 
This amendment is prompted by reports indicating that some locking tab 
washers on the roller attach bolt could fail, due to the absence of an 
inner tang. The actions specified by this AD are intended to prevent 
the loss of roller attach nuts and the flap roller, which could result 
in the loss of a flap when the airplane is subject to load limit 
conditions, and consequently lead to reduced controllability of the 
airplane.

DATES: Effective January 24, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 24, 1997.

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Aircraft Company, Manager Service Engineering, 
Hawker Customer Support Department, P.O. Box 85, Wichita, Kansas 67201-
0085. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita 
Aircraft Certification Office, Small Airplane Directorate, 1801 Airport 
Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Larry Engler, Aerospace Engineer, 
Airframe Branch, ACE-115W, FAA, Wichita Aircraft Certification Office, 
Small Airplane Directorate, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4122; fax (316) 
946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 94-14-06, 
amendment 39-8958 (59 FR 35234, July 11, 1994), which is applicable to 
certain Raytheon (Beech) Model 400A and 400T (military T-1A) series 
airplanes, was published in the Federal Register on September 30, 1996 
(61 FR 51064). The action proposed to supersede AD 94-14-06 to require 
the following actions:
    1. For airplanes that have been inspected previously, and on which 
the washers, tab washers, and flat washers have been installed in 
accordance with AD 94-14-06: Those washers would be required to be 
replaced with new washers (including stronger tab washers).
    2. For airplanes that have not been inspected previously and have 
not had the washers, tab washers, and flat washers replaced; and for 
airplanes that were not included in the applicability of AD 94-14-06: 
These airplanes would be required to be inspected for discrepancies in 
the roller attach nuts and bolts of the flaps, and discrepant parts 
replaced. In addition, the new washers, including the stronger tab 
washers, would be required to be installed on the attach bolts.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.
    The FAA has revised the final rule to specify that the type 
certificate holder for the affected airplanes has been changed from the 
Beech Aircraft Corporation to Raytheon Aircraft Company.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 212 Raytheon (Beech) Model 400A and 400T 
series airplanes of the affected design in the worldwide fleet. The FAA 
estimates that 183 airplanes of U.S. registry will be affected by this 
AD.
    It is estimated that 102 of the U.S.-registered airplanes will be 
required to have the washers replaced with new and stronger washers. 
This action will take approximately 2 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Required 
parts will cost approximately $25 per airplane. Based on these figures, 
the cost impact of the required replacement action on U.S. operators of 
these airplanes is estimated to be $14,790, or $145 per airplane.
    It is estimated that 81 of the U.S.-registered airplanes will be 
required to be inspected for discrepancies of the roller attach nuts 
and bolts, and will require the installation of new washers. Those 
actions will take approximately 6 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Required 
parts will cost approximately $100 per airplane. Based on these 
figures, the cost impact of the required actions on U.S. operators of 
these airplanes is estimated to be $37,260, or $460 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.

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.
    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 final evaluation has been prepared for this action 
and it 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.

[[Page 67197]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-8958 (59 FR 
35234, July 11, 1994), and by adding a new airworthiness directive 
(AD), amendment 39-9845, to read as follows:

96-25-03  Raytheon Aircraft Company (Formerly Beech): Amendment 39-
9845. Docket 96-NM-158-AD. Supersedes AD 94-14-06, Amendment 39-
8958.

    Applicability: Model 400A and 400T series airplanes; as listed 
in Beech Service Bulletin No. 2522, dated January 1994, and Raytheon 
Service Bulletin No. 2522, Revision 1, dated May 1996; certificated 
in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (d) 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, unless accomplished 
previously.
    To prevent loss of roller attach nuts and the flap roller, which 
could result in the loss of a flap when the airplane is subject to 
load limit conditions, and consequently lead to reduced 
controllability of the airplane, accomplish the following:
    (a) For airplanes listed in Beech Service Bulletin No. 2522, 
dated January 1994, on which the inspection and installation of 
washers, tab washers, and flat washers have been accomplished prior 
to the effective date of this AD in accordance with that service 
bulletin, and in accordance with the requirements of AD 94-14-06, 
amendment 39-8958: Prior to the accumulation of 200 hours time-in-
service or within one year after the effective date of this AD, 
whichever occurs first, remove the washers, tab washers, and flat 
washers, having part numbers specified in Table 1 of this AD, from 
the roller attach bolts of the left and right flaps, and replace 
them with new washers, tab washers, and flat washers, having part 
numbers specified in Table 2 of this AD, in accordance with Part I 
of Raytheon Service Bulletin No. 2522, Revision 1, dated May 1996.

                     Table 1.--Parts To Be Replaced                     
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                  Part                            Beech part No.        
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Tab Washers............................  NAS460-616                     
                                         MS27111-3                      
                                         168AS-06-02                    
Flat Washers...........................  AN960D616L                     
Washers................................  AN960-616                      
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                     Table 2.--New Replacement Parts                    
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                  Part                            Beech part No.        
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Tab Washers............................  45A16122-37                    
Flat Washers...........................  AN960D616L                     
Washers................................  AN960-616                      
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    (b) For all other airplanes not subject to paragraph (a) of this 
AD: Prior to the accumulation of 200 hours time-in-service after the 
effective date of this AD, or within one year after the effective 
date of this AD, whichever occurs first, accomplish the actions 
specified in paragraphs (b)(1) and (b)(2) of this AD:
    (1) Perform an inspection of the roller attach nuts and bolts 
for the flaps to detect discrepancies (i.e., flattened, worn or 
damaged threads, damaged keway of bolts, etc.), in accordance with 
Part II of Raytheon Service Bulletin No. 2522, Revision 1, dated May 
1996. If any discrepancies are found, prior to further flight, 
replace the discrepant parts with new or serviceable parts, in 
accordance with the service bulletin. And
    (2) Remove the washers, tab washers, and flat washers from the 
roller attachment bolts of the left and right flaps, and replace 
them with new washers, tab washers, and flat washers that have part 
numbers specified in Table 2 of this AD, in accordance with Part I 
of Raytheon Service Bulletin No. 2522, Revision 1, dated May 1996.
    (c) As of the effective date of this AD, no person shall install 
on any airplane any tab washer for the roller attach bolt, having 
Beech part number 168AS-06-2, NAS460-616, or MS27111-3.
    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Wichita Aircraft Certification 
Office (ACO), FAA, Small Airplane Directorate. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Wichita ACO.

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

    (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) The actions shall be done in accordance with Raytheon 
Service Bulletin No. 2522, Revision 1, dated May 1996. 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 Raytheon Aircraft Company, Manager 
Service Engineering, Hawker Customer Support Department, P.O. Box 
85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Wichita Aircraft Certification Office, 
Small Airplane Directorate, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (g) This amendment becomes effective on January 24, 1997.

    Issued in Renton, Washington, on December 2, 1996.
Gary L. Killion,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-31114 Filed 12-19-96; 8:45 am]
BILLING CODE 4910-13-U