AD 94-04-18

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AD Number:
94-04-18
Document Type:
AD Final Rules
Docket Number:
93-CE-49-AD
Subject Heading:
Airworthiness Directives: Beech Aircraft Corporation Models 34C, T34C, and T34C-1 Airplanes
Subject:
Elevator Arm Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/12/1994
Make:
Textron Aviation Inc.
Model:
T-34C
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39 [59 FR 13439 NO. 55 03/22/94]
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 94-04-18
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   93-CE-49-AD

AMENDMENT:   39-8838

AD NUMBER:   94-04-18

SUBJECT HEADING:   Airworthiness Directives: Beech Aircraft Corporation Models 34C, T34C, and T34C-1 Airplanes

ACTION:   Final rule

SUMMARY:   This amendment supersedes Airworthiness Directive (AD) 92-24-01, which currently requires inspecting the elevator balance arm assemblies of certain Beech Aircraft Corporation Models 34C and T34C-1 airplanes to ensure that sufficient welds exist to secure the balance weight tube to the attachment plate, and also requires replacing the assembly if insufficient welds are found. The Federal Aviation Administration (FAA) has determined that the existing AD should also apply to certain Beech Model T34C airplanes. This action retains the requirements of AD 92-24-01 and incorporates these Beech Model T34C airplanes. The actions specified by this AD are intended to prevent separation of an elevator balance arm assembly from the elevator because of an insufficient weld, which could result in loss of control of the airplane.

DATES:   Effective April 12, 1994. The incorporation by reference of Beech Service Bulletin No. 2442, dated May 1992, was previously approved by the Director of the Federal Register as of December 15, 1992. The incorporation by reference of Beech Service Bulletin No. 2442, Revision 1, dated August 1993, is approved by the Director of the Federal Register as of April 12, 1994.

ADDRESSES:   Service information that applies to this AD may be obtained from the Beech Aircraft Corporation, 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, 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:   Mr. Larry Engler, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4122; facsimile (316) 946-4407.

SUPPLEMENTARY INFORMATION:   A proposal to amend part 39 of the Federal Aviation Regulations to include an AD that would apply to certain Beech Models 34C, T34C, and T34C-1 airplanes was published in the Federal Register on November 1, 1993 (58 FR 58310). The action proposed to supersede AD 92-24-01 with a new AD that would (1) retain the requirements for the Models 34C and T34C-1 airplanes of inspecting the balance arm assemblies to ensure that sufficient welds exist to secure the balance weight tube to the attachment plate, and replacing any balance arm assemblies with insufficient welds; and (2) incorporate the Model T34C airplanes into the effectivity of that AD. The proposed inspections would be accomplished in accordance with Beech Service Bulletin (SB) No. 2442, dated May 1992, or Beech SB No. 2442, Revision 1, dated September 1993. The balance arm assembly replacement, if required, would be accomplished in accordance with the applicable maintenance manual.

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.

After careful review of all available information, 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 nor add any additional burden upon the public than was already proposed.

The FAA estimates that 495 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 $55 an hour. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $54,450. AD 92-24-01, which will be superseded by this AD, currently requires the same actions for 142 of the affected airplanes. This AD requires these inspections for an additional 353 airplanes, assuming that none of the airplane operators of these 353 airplanes have already inspected the elevator balance arm assemblies. Based on the above information, the cost impact of this AD is $38,830 over that already required by AD 92-24-01.

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 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. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89.

Section 39.13 - [AMENDED]
2. Section 39.13 is amended by removing AD 92-24-01, Amendment 39-8406, and adding the following new AD to read as follows:

REGULATORY TEXT:  
94-04-18 BEECH AIRCRAFT CORPORATION: Amendment 39-8838; Docket No. 93-CE- 49-AD. Supersedes AD 92-24-01, Amendment 39-8406.

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

Models	Serial Numbers
34C	GP-1 through GP-50;
T34C	GL-1 through GL-353;
T34C-1	GM-1 through GM-71 and
GM-78 through GM-98.

Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished (compliance with AD 92-24-01).

To prevent separation of an elevator balance arm assembly from the elevator because of insufficient welds, which could result in loss of control of the airplane, accomplish the following:

(a) Inspect each elevator balance arm assembly to ensure that sufficient welds exist to secure the balance weight tube to the attachment plate. Perform this inspection in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of either Beech Service Bulletin No. 2442, dated May 1992, or Beech Service Bulletin No. 2442, Revision 1, dated September 1993.

(b) If an insufficient weld is found during the inspection required by paragraph (a) of this AD, prior to further flight, replace the subject elevator balance arm assembly in accordance with Chapter 27-30 of the applicable maintenance manual.

(c) 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.

(d) 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), FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita ACO.

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

(e) The inspection required by this AD shall be done in accordance with either Beech Service Bulletin No. 2442, dated May 1992, or Beech Service Bulletin No. 2442, Revision 1, dated September 1993. The incorporation by reference of Beech Service Bulletin No. 2442, dated May 1992, was previously approved by the Director of the Federal Register as of December 15, 1992. The incorporation by reference of Beech Service Bulletin No. 2442, Revision 1, dated August 1993 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 Beech Aircraft Corporation, 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.

(f) This amendment (39-8838) supersedes AD 92-24-01, Amendment 39-8406.

(g) This amendment becomes effective on April 12, 1994.

FOOTER: