[Federal Register Volume 62, Number 53 (Wednesday, March 19, 1997)]
[Rules and Regulations]
[Pages 12949-12951]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-6539]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-CE-34-AD; Amendment 39-9967; AD 97-06-10]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 91-14-
14, which currently requires repetitively inspecting the main landing 
gear (MLG) ``A'' frame assemblies for cracks on Raytheon Aircraft 
Company (Raytheon) Model 76 airplanes (formerly referred to as Beech 
Model 76 airplanes), and replacing any assembly found cracked. AD 91-
14-14 resulted from reports of fatigue cracks developing on the MLG 
``A'' frame assemblies of the affected airplanes. 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 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 this 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: Effective May 16, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 16, 1997.

ADDRESSES: Service information that applies to this AD may be obtained 
from the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085. This information may also be examined at 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; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.


[[Page 12950]]


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:

Events Leading to the Issuance of the This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to Raytheon Model 76 
airplanes (formerly referred to as Beech Model 76 airplanes) was 
published in the Federal Register as a notice of proposed rulemaking 
(NPRM) on October 18, 1996 (61 FR 54368). The NPRM proposed to 
supersede AD 91-14-14 with a new AD that 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 as specified in the NPRM would be in accordance 
with Raytheon Mandatory Service Bulletin No. 2361, Revision III, dated 
June 1996.
    The NPRM was the result of Raytheon developing improved design MLG 
``A'' frame assemblies, and the FAA determining 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.
    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.

The FAA's Determination

    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.

Cost Impact

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

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 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 USC 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:

97-06-10  Raytheon Aircraft Company (formerly Beech Aircraft 
Corporation): Amendment 39-9967; 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 initally 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 
Mandatory 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

[[Page 12951]]

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 
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.
    (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) The inspection required by this AD shall be done in 
accordance with Raytheon Mandatory Service Bulletin No. 2361, 
Revision III, dated June 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 the 
Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085. 
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.
    (g) This amendment (39-9967) supersedes AD 91-14-14, Amendment 
39-7055.
    (h) This amendment (39-9967) becomes effective on May 16, 1997. 
Issued in Kansas City, Missouri, on March 6, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-6539 Filed 3-18-97; 8:45 am]
BILLING CODE 4910-13-U