AD 96-03-13

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AD Number:
96-03-13
Document Type:
AD Final Rules
Docket Number:
95-CE-32-AD
Subject Heading:
Airworthiness Directives; Beech Aircraft Corporation F90, 99, 99A, A99A, B99, C99, 100, A100, B100, ...Show more
Subject:
Main Landing Gear Drag Leg Lock Link
Status:
Current
Citation:
Federal Register: February 22, 1996 (Volume 61, Number 36)
Citation Publish Date:
02/22/1996
Effective Date:
04/01/1996
Make:
Textron Aviation Inc.
Model:
100 | 200 | 200C | 200CT | 200T | 65-A90-2 | 65-A90-3 | 99 | 99A | A100 | A100-1 (U-21J) | A200 (C-1...Show more
Product Type:
Aircraft
Product Subtype:
Small/Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39 [61 FR 6768 NO. 36 02/22/96]
Comments:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 96-03-13
CITATION:   [Federal Register: February 22, 1996 (Volume 61, Number 36)]

PAGE NUMBER:   [Page 6768]

DOCKET NUMBER:   95-CE-32-AD

AMENDMENT:   39-9510

AD NUMBER:   96-03-13

SUBJECT HEADING:   Airworthiness Directives; Beech Aircraft Corporation F90, 99, 99A, A99A, B99, C99, 100, A100, B100, 200, B200, 200T, B200T, 200C. B200C, 200CT. B200CT, 65-A90-2, 65-A90-3, A200, A200C, and A200CT Series Airplanes

ACTION:   Final rule

SUMMARY:   This amendment adopts a new airworthiness directive (AD) that applies to Beech Aircraft Corporation (Beech) 90, 99, 100, and 200 series airplanes. This action requires inspecting the main landing gear drag leg lock link to ensure that the hole for the roll pin is drilled completely through both walls of the main landing gear drag leg lock link and, if not drilled completely through both link walls, replacing any main landing gear drag leg lock link. An incident in which the left main landing gear collapsed on one of the affected airplanes prompted this action. Investigation revealed that the roll pin hole was not completely drilled through both walls of the drag leg lock link. The actions specified by this AD are intended to prevent main landing gear collapse caused by drag leg lock link failure, which could result in loss of control of the airplane.

DATES:   Effective April 1, 1996. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 1, 1996.

ADDRESSES:   Service information that applies to this AD may be obtained from Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. This information may also be examined at the Federal Aviation Administration (FAA), Central Region, Office of the Assistant Chief Counsel, Attention: Rules Docket 95-CE-32-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:   Mr. Steve Potter, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4124; facsimile (316) 946-4407.

SUPPLEMENTARY INFORMATION:   A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to Beech Aircraft Corporation 90, 99, 100, and 200 series airplanes was published in the Federal Register on August 16, 1995 (60 FR 42479). The action proposed to require inspecting the main landing gear drag leg lock link to ensure that the hole for the roll pin is drilled through both walls of the link and, if not drilled completely through both link walls, replacing any main landing gear drag leg lock link. Accomplishment of the proposed action would be in accordance with Beech Service Bulletin No. 2607, Revision 1, dated April 1995.

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 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.

The FAA estimates that 2,229 airplanes in the U.S. registry will be affected by this AD action, that it will take approximately 5 work hours per airplane to accomplish this action, and that the average labor rate is approximately $60 an hour. Parts cost approximately $100 per airplane. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $891,600. This figure is based on the assumption that all of the affected airplanes have incorrectly drilled drag leg lock links and that none of the owners/operators of the affected airplanes have replaced the incorrectly drilled links.

Beech has informed the FAA that parts have been distributed to equip approximately 648 airplanes. Assuming that these distributed parts are incorporated on the affected airplanes, the cost of the proposed AD would be reduced by $259,200 from $891,600 to $632,400. In addition, the FAA believes that a majority of the affected airplanes will not have incorrectly drilled links, thereby further reducing the cost impact of the proposed AD upon the public.

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.

Section 39.13 - [AMENDED]
2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows:

REGULATORY TEXT:  
96-03-13 BEECH AIRCRAFT CORPORATION: Amendment 39-9510; Docket No. 95-CE-32-AD

Applicability: The following airplane models and serial numbers, certificated in any category:

Models	Serial Numbers
F90	LA-2 through LA-236
99, 99A, A99A, B99,	U-1 through U-239 and C99
100 and A100	B-1 through B-94 and B-100 through B-247
B100	BE-1 through BE-137
200 and B200	BB-2, BB-6 through BB-1157,
BB-1159 through BB-1166, and
BB-1168 through BB-1192
200T and B200T	BT-1 through BT-30
200C and B200C	BL-1 through BL-72
200CT and B200CT	BN-1 through BN-4
65-A90-2(RU-21B)	LS-1 through LS-3
65-A90-3(RU-21C)	LT-1 through LT-2
200 (A100-1)	BB-3 through BB-5
A100 (U-21F)	B-95 through B-99
A200 (C-12A and C-12C)	BC-1 through BC-75, and BD-1
through BD-30
A200C (UC-12B)	BJ-1 through BJ-66
A200CT (C-12D)	BP-1, BP-22, and BP-24 through BP-45
A200CT (FWC-12D)	BP-7 through BP-11
A200CT (RC-12D)	GR-1 through GR-13
A200CT (RC-12H)	GR-14 through GR-19
A200CT (RC-12G)	FC-1 through FC-3

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 (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 within the next 100 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished.

To prevent main landing gear collapse caused by drag leg lock link failure, which could result in loss of control of the airplane, accomplish the following:

(a) Inspect the main landing gear drag leg lock link to ensure that the hole for the roll pin is drilled completely through both walls of the link in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin No. 2607, Revision 1, dated April 1995.

(b) Prior to further flight, replace any drag leg lock link that does not have the roll pin hole drilled through both walls of the link. Accomplish this replacement in accordance with the applicable maintenance manual.

(c) 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.

(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, FAA, 1801 Airport Road, 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 Aircraft Certification Office.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office.

(e) The inspections and replacements required by this AD shall be done in accordance with Beech Service Bulletin No. 2607, Revision 1, dated April 1995. 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 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., 7th Floor, suite 700, Washington, DC.

(f) This amendment becomes effective on April 1, 1996.

FOOTER: