[Federal Register Volume 61, Number 203 (Friday, October 18, 1996)]
[Proposed Rules]
[Pages 54368-54370]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-26704]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-CE-34-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Corporation (Formerly 
Beech Aircraft Corporation) Model 76 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to supersede Airworthiness Directive 
(AD) 91-14-14, which currently requires repetitively inspecting the 
main landing gear (MLG) ``A'' frame assemblies for cracks on Raytheon 
Aircraft Corporation (Raytheon) Model 76 airplanes, and replacing any 
assembly found cracked. Reports of fatigue cracks developing on the MLG 
``A'' frame assemblies of the affected airplanes prompted AD 91-14-14. 
Raytheon has developed improved design MLG ``A'' frame assemblies, and 
the Federal Aviation Administration (FAA) has determined that Model 76 
airplanes with an improved design ``A'' frame assembly installed on 
both the left and right MLG should be exempt from AD 91-14-14. This 
proposed action retains the requirement of repetitively inspecting the 
MLG ``A'' frame assemblies for cracks and replacing any cracked ``A'' 
frame assembly only for those Model 76 airplanes that do not have the 
improved design parts installed. The actions specified by the proposed 
AD are intended to prevent MLG failure because of a cracked ``A'' frame 
assembly, which could result in loss of control of the airplane during 
landing operations.

DATES: Comments must be received on or before December 20, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 94-CE-34-AD, Room 1558, 601 E. 
12th Street, Kansas City, Missouri 64106. Comments may be inspected at 
this location

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between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
    Service information that applies to the proposed AD may be obtained 
from the Raytheon Aircraft Corporation, P.O. Box 85, Wichita, Kansas 
67201-0085. This information also may be examined at the Rules Docket 
at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Larry Engler, Aerospace Safety 
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 
946-4122; facsimile (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 94-CE-34-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Central Region, Office of the Assistant Chief Counsel, 
Attention: Rules Docket No. 94-CE-34-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.

Discussion

    AD 91-14-14, Amendment 39-7055 (56 FR 29173, June 26, 1991), 
currently requires repetitively inspecting the main landing gear (MLG) 
``A'' frame assemblies for cracks on Raytheon Model 76 airplanes, and 
replacing any MLG ``A'' frame assembly found cracked. Accomplishment of 
the inspections required by AD 91-14-14 is in accordance with Beech 
Service Bulletin (SB) No. 2361, dated February 1991.
    Reports of fatigue cracks developing on the MLG ``A'' frame 
assemblies of the affected airplanes prompted AD 91-14-14. Since the 
issuance of AD 91-14-14, Raytheon has developed improved design MLG 
``A'' frame assemblies, part number (P/N) 105-810023-75 (left) and P/N 
105-810023-76 (right).

Applicable Service Information

    Raytheon has revised SB No. 2361 to the Revision III level (dated 
June 1996). This SB revision specifies procedures for inspecting the 
MLG ``A'' frame assemblies for cracks, and introduces the improved 
design MLG ``A'' frame assemblies, P/N 105-810023-75 (left) and P/N 
105-810023-76 (right).

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, including the 
referenced service information, the FAA has determined that (1) 
Raytheon Model 76 airplanes incorporating an improved MLG ``A'' frame 
assembly on both the left and right MLG should be exempt from the 
inspections currently required by AD 91-14-14; and (2) AD action should 
be taken to prevent MLG failure because of a cracked ``A'' frame 
assembly, which could result in loss of control of the airplane during 
landing operations.

Explanation of the Provisions of the Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Raytheon Model 76 airplanes of the same type 
design, the proposed AD would supersede AD 91-14-14 with a new AD. The 
proposed action would retain the requirement of repetitively inspecting 
the MLG ``A'' frame assemblies for cracks and replacing any part found 
cracked, but would exempt those airplanes with both a P/N 105-810023-75 
(left) and P/N 105-810023-76 (right) MLG ``A'' frame assembly 
installed. Accomplishment of the proposed repetitive inspections would 
be in accordance with Beech SB No. 2361, Revision III, dated June 1996.

Cost Impact

    The FAA estimates that 437 airplanes in the U.S. registry would be 
affected by the proposed AD, that it would take approximately 2 
workhours per airplane to accomplish the proposed initial inspection, 
and that the average labor rate is approximately $60 an hour. Based on 
these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $52,440. This figure only takes into 
account the cost of the proposed initial inspection; repetitive 
inspection costs and costs for replacing any cracked MLG ``A'' frame 
assemblies are not included in this figure. The FAA has no way of 
determining how many airplanes would have cracked MLG ``A'' frame 
assemblies or how many repetitive inspections each affected owner/
operator would incur over the life of the airplane.
    The only difference between the proposed AD and AD 91-14-14 is that 
the proposed AD would exempt airplanes with the improved MLG ``A'' 
frame assemblies installed. Therefore, the cost impact of the proposed 
AD is less than that already required by AD 91-14-14 because some 
airplanes will have the improved MLG ``A'' frame assemblies installed.

Regulatory Impact

    The regulations proposed herein would 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 
proposal would 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) if promulgated, 
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 draft regulatory evaluation 
prepared for this action has been placed 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, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the

[[Page 54370]]

Administrator, the Federal Aviation Administration proposes to amend 14 
CFR part 39 of the Federal Aviation Regulations 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) 91-14-14, Amendment 39-7055 (56 FR 29173, June 26, 1991), and by 
adding a new AD to read as follows:

Raytheon Aircraft Corporation (formerly Beech Aircraft Corporation): 
Docket No. 94-CE-34-AD; Supersedes AD 91-14-14, Amendment 39-7055.

    Applicability: Model 76 airplanes (serial numbers ME-1 through 
ME-437), certificated in any category, that do not have both a part 
number (P/N) 105-810023-75 (left) and P/N 105-810023-76 (right) main 
landing gear (MLG) ``A'' frame assembly installed.

    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 (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 the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required within the next 50 hours time-in-service 
(TIS) after the effective date of this AD, unless already 
accomplished (compliance with AD 91-14-14), and thereafter at 
intervals not to exceed 100 hours TIS .
    To prevent MLG failure because of a cracked ``A'' frame 
assembly, which could result in loss of control of the airplane 
during landing operations, accomplish the following:
    (a) Inspect, using both visual and dye penetrant methods, both 
the left and right MLG ``A'' frame assemblies for cracks in 
accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Raytheon 
Service Bulletin No. 2361, Revision III, dated June 1996. Pay 
particular attention to the tips of the gussets and the small 
corrosion treatment hole adjacent to the gusset.
    (b) If any MLG ``A'' frame assembly is found cracked during any 
inspection required by this AD, prior to further flight, replace the 
assembly with one of the following in accordance with Chapter 32 of 
the Raytheon Model 76 Maintenance Manual:
    (1) A new MLG ``A'' frame assembly with the same P/N as that 
found cracked. The 100-hour TIS repetitive inspection requirement 
still applies when this design ``A'' frame is installed.
    (2) A P/N 105-810023-75 (left) or P/N 105-810023-76 (right) main 
MLG ``A'' frame assembly, as applicable. Repetitive inspections are 
no longer required on an MLG ``A'' frame assembly incorporating this 
design configuration. Repetitive inspections are still required on 
an MLG ``A'' frame assembly if it does not incorporate this improved 
design configuration.
    (c) Installing both P/N 105-810023-75 (left) and P/N 105-810023-
76 (right) MLG ``A'' frame assemblies eliminates the repetitive 
inspection requirement of this AD.
    (d) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the airplane to a location where 
the requirements of this AD can be accomplished.
    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an equivalent level of safety may be 
approved by the Manager, Wichita Aircraft Certification Office 
(ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, 
Kansas 67209. The request shall be forwarded through an appropriate 
FAA 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.

    (f) All persons affected by this directive may obtain copies of 
the document referred to herein upon request to the Raytheon 
Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085; or 
may examine this document at the FAA, Central Region, Office of the 
Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, 
Missouri 64106.
    (g) This amendment supersedes AD 91-14-14, Amendment 39-7055.

    Issued in Kansas City, Missouri, on October 10, 1996.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-26704 Filed 10-17-96; 8:45 am]
BILLING CODE 4910-13-U