AD 91-17-01

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AD Number:
91-17-01
Document Type:
AD Final Rules
Docket Number:
90-CE-71-AD
Subject Heading:
Airworthiness Directives; Beech: Models 35-33, 35-A33, 35-B33, 35-C33, E33, F33, G33, 35-C33A, E33A...Show more
Subject:
Elevator Trim Tab Actuators
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/25/1991
Make:
Textron Aviation Inc.
Model:
35-33 | 35-A33 | 35-B33 | 35-C33 | 35-C33A | 36 | 45 (Military YT-34) | 56TC | 58 | 58A | 58P | 58PA...Show more
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Superseded AD: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Superseded By: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
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 91-17-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-CE-71-AD

AMENDMENT:   39-7099

AD NUMBER:   91-17-01

SUBJECT HEADING:   Airworthiness Directives; Beech: Models 35-33, 35-A33, 35-B33, 35-C33, E33, F33, G33, 35-C33A, E33A, F33A, E33C, F33C, 36, A36, A36TC, B36TC, T34C-1, 34C, T-34C, 45, A45, D45, 95, B95, B95A, D95A, E95, 95-55, 95-A55, 95-B55, 95-B55A, 95-C55, 95-C55A, D55, D55A, E55, E55A, 56TC, A56TC, 58, 58A, 58P, 58PA, 58TC, and 58TCA Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 25, 1991

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
91-17-01 BEECH: Amendment 39-7099. Docket No. 90-CE-71-AD.

Applicability: The following Model airplanes, certificated in any category:

Models	Serial Numbers
35-33, 35-A33, 35-B33,	CD-1 through CD-981 and
35-C33, E33, F33, G33	CD-983 through CD-1304
35-C33A, E33A, F33A	CE-1 through CE-235,
CE-249, CE-250, CE-256,
CE-260, CE-264 through CE-268, and
CE-270 through CE-1565
E33C, F33C	CJ-1 through CJ-179
36, A36	E-1 through E-2103, E-2105 through E-2110
A36TC, B36TC	EA-1 through EA-319, and EA-321 through
EA-388
T34C-1	GM-1 through GM-142
34C	GP-1 through GP-50
T-34C	GL-1 through GL-353
45	G-3 through G-6
A45	G-7 through G-156,
G-257 through G-306, G-696 through G-845,
CG-1 through CG-47, CG-58 through CG-60,
CG-68, CG-73, CG-75, CG-78, CG-79, CG-105,
CG-106, CG-108, CG-111 through CG-179,
CG-200 through CG-223, CG-279 through
CG-319
D45	BG-1 through BG-423
95	TD-2 through TD-302
B95	TD-303 through TD-452
B95A	TD-453 through TD-533
D95A	TD-534 through TD-707
E95	TD-708 through TD-721
95-55	TC-1 through TC-190
95-A55	TC-191 through TC-349, TC-351 through
TC-370, and TC-372 through TC-501
95-B55, 95-B55A	TC-371, TC-502 through TC-2456
95-C55	TC-350
95-C55A	TE-1 through TE-49, and TE-51 through TE-451
D55, D55A	TE-452 through TE-767
E55, E55A	TE-768 through TE-1201
56TC	TG-2 through TG-83
A56TC	TG-84 through TG-94
58, 58A	TH-1 through TH-1388, and TH-1390 through TH-1395
58P, 58PA	TJ-3 through TJ-435, and TJ-437 through TJ-443
58TC, 58TCA	TK-1 through TK-150

Compliance: Required the next time the elevator trim tab actuators are removed for any reason, but no later than 12 calendar months after the effective date of this AD, unless already accomplished.

To prevent loss of control of the airplane because of interchanging the right-hand and left-hand elevator trim tab actuators, accomplish the following:

(a) Paint a stripe on each stabilizer rear spar (right-hand black; and left-hand blue) in accordance with the Accomplishment Instructions of Beech Service Bulletin No. 2399, dated March 1991.

(b) Remove the cover over the actuator inspection hole on each stabilizer and paint the inspection hole ledges (right-hand black; and left-hand blue) in accordance with the Accomplishment Instructions of Beech Service Bulletin No. 2399, dated March 1991.

(c) Paint a stripe .50 by 1 inch on each actuator housing through the inspection holes (right-hand black; and left-hand blue) in accordance with the Accomplishment Instructions in Beech Service Bulletin No. 2399, dated March 1991. Actuators must not be removed to paint the .50 by 1 inch stripe on the housing.

NOTE: A left-hand trim tab actuator will have threads on its actuator screw that will rotate clockwise when screwed into the actuator assembly, and a right-hand trim tab actuator will have threads on its actuator screw that will rotate counterclockwise when screwed into the actuator assembly.

(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes 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, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office.

(f) The modification required by this AD shall be done in accordance with Beech Service Bulletin No. 2399, dated March 1991. 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 Beech Aircraft Corporation, Commercial Service, Department 52, 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, 1100 L Street, NW, Room 8401, Washington, DC.

This amendment (39-7099, AD 91-17-01) becomes effective on November 25, 1991.

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