AD 87-04-24

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AD Number:
87-04-24
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Beech Model 65-A90, B90, C90, C90A, E90, F90, 200, B200, 200C, B200C, 200...Show more
Subject:
Elevator Trim Cable System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/14/1987
Make:
Textron Aviation Inc.
Model:
1900 | 1900C | 200 | 200C | 200CT | 200T | 300 | 65-A90 | 65-A90-1 | 65-A90-2 | 65-A90-3 | 65-A90-4 ...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Superseded AD: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Superseded By: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
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 87-04-24
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5599

AD NUMBER:   87-04-24

SUBJECT HEADING:   Airworthiness Directives; Beech Model 65-A90, B90, C90, C90A, E90, F90, 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, 300, 1900, 1900C, H90, A200, A200C, A200CT, B200C, 65-A90-1, 65-A90-2, 65-A90-3 and 65-A90-4 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 14, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
87-04-24 BEECH AIRCRAFT CORPORATION: Amendment 39-5599. Applies to the following Beech airplanes certificated in any category.

MODEL	SERIAL NUMBERS S/N	REFERENCE SERVICE
INSTRUCTION NO.
65-A90, B90,	LJ-114 thru LJ-1139;	Beechcraft Mandatory
C90, C90A;		Service Instruction
E90;	LW-1 thru LW-347;	No. 2028, Rev. III,
F90;	LA-2 thru LA-236	revised February 1987
200, B200;	BB-2; BB-6 thru BB-1211;
BB-1213 thru BB-1253;
BB-1255 thru BB-1261;
BB-1263 thru BB-1267;	
200C, B200C;	BL-1 thru BL-112 and
BL-124 thru BL-127;	
200CT, B200CT;	BN-1 thru BN-4;	
200T, B200T	BT-1 thru BT-31;	
300	FA-1 thru FA-38 and
FA-40 thru FA-50	
1900	UA-1 thru UA-3	
1900C	UB-1 thru UB-62	
H90 (T-44A)	LL-1 thru LL-18,
LL-20 thru LL-31,
LL-33 thru LL-40,
LL-42 thru LL-48, and
LL-50 thru LL-61	Beech T-44A Service
Instructions No.
T-44A-0058, Rev. 1
A200 (C-12A)	BD-1 thru BD-30;	Beech C-12 Service
A200 (C-12C)	BC-1 thru BC-75;	Instructions No.
A200CT (C-12D)	BP-1, BP-22, BP-24 thru BP-39;
BP-40 and BP-45;	C-12-0103, Rev. 1
A200CT (RC-12D)	GR-1 thru GR-13;	
A200CT (RC-12G)	FC-1 thru FC-3;	
A200CT (FWC-12D)	BP-7 thru BP-11;	
A200C (UC-12B)	BJ-1 thru BJ-66	
A200CT (C-12D)	BP-46 thru BP-51;	Beech C-12 Service
A200CT (C-12F)	BP-52 thru BP-63;	Instructions No.
B200C (C-12F)	BL-73 thru BL-112 and
BL-118 thru BL-123;	C-12-0112
65-A90-1 (U-21A)	LM-1 thru LM-63,
LM-65, LM-67 thru LLM-69,
LM-71 thru LM-107,
and LM-112 thru LM-124;	Beech U-21 Service
Instruction No.
U-21-0002, Rev. 1
65-A90-1 (JU-21A)	LM-64, LM-66, LM-70;	
65-A90-1 (U-21G)	LM-125 thru LM-141;	
5-A90-1 (RU-21A)	LM-108 thru LM-111;	
6 65-A90-2 (RU-21B)	LS-1 thru LS-3;	
65-A90-3 (RU-21C)	LT-1 and LT-2;	
65-A90-4 (RU-21H)	LU-1 thru LU-16	
Compliance: Required as indicated after the effective date of this AD, unless previously accomplished.

To preclude malfunction of the elevator trim cable system, accomplish the following:

(a) Within the next 10 hours time-in-service, perform the following:

(1) For Models 65-A90, B90, C90, C90A airplanes (S/N LJ-114 thru LJ-1110), and Model E90 airplanes (S/N LW-1 thru LW-347), which have complied with AD 86-20- 03, paragraph (b), and for Models C90A airplanes (S/N LJ-1111 thru LJ-1139), which have a redesigned elevator trim cable system installed at the Beech factory without moisture protection; modify the elevator trim system in accordance with Part IV of Beechcraft Service Bulletin No. 2028, Rev. III, dated February 1987.

(2) For Models F90 airplanes (S/N LA-2 and LA-235); Models 200 and B200 airplanes (S/N BB-2, BB-6 thru BB-1211 and BB-1213 thru BB-1217); and for Models 200C and B200C airplanes (S/N BL-1 thru BL-112 and BL-124); and for Models 200CT and B200CT airplanes (S/N BN-1 thru BN-4); and for Models 200T and B200T airplanes (S/N BT-1 thru BT-30), which have complied with AD 86-20-03, paragraph (b), and for Models F90 airplane (S/N LA-236); and for Models 200 and B200 airplanes (S/N BB-1218 thru BB-1253, BB-1255 thru BB-1261, BB-1263 thru BB-1267); and for Models B200C airplanes (S/N BL-125 thru BL-127); and for Models B200T airplane (S/N BT-31), which have a redesigned elevator trim cable system installed at the Beech factory without moisture protection; modify the elevator trim system in accordance with Part V of Beechcraft Service Bulletin No. 2028, Rev. III, dated February 1987.

(3) For Models 1900 airplanes (S/N UA-1 thru UA-3) and for Models 1900C airplanes (S/N UB-1 thru UB-44), which have complied with AD 86-20-03, paragraph (b), and for Models 1900C airplanes (S/N UB-45 thru UB-62), which have a redesigned elevator trim cable system installed at the Beech factory without moisture protection; modify the elevator trim system in accordance with Part VI of Beechcraft Service Bulletin No. 2028, Rev. III, dated February 1987.

(b) For those airplanes that have not been modified in accordance with paragraph (b) of AD 86-20-03, within the next 25 hours time-in-service, accomplish the following:

(1) Check the operation of the elevator trim system and mark the elevator trim indicator scale in accordance with Part I or Part II of Beech Service Bulletin No. 2028, Rev. III, dated February 1987.

(2) For Models 65-A90, B90, C90, C90A, and E90 airplanes, mark the elevator trim tab push rods in accordance with Part I or Part II of Beech Service Bulletin No. 2028, Rev. III, dated February 1987.

NOTE: The following airplanes have been previously marked by the manufacturer per paragraphs (a)(1) and (a)(2) of AD 86-20-03: Models C90A (S/N LJ-1077 thru LJ-1110), F90 (S/N LA-223 thru LA-235), B200 (S/N BB-1193 thru BB-1217), B200C (S/N BL-72 thru BL-112 and BL-124), 300 (S/N FA-1 thru FA-38 and FA-40 thru FA-50), 1900 (S/N UA-1 thru UA-3), and 1900C (S/N UB-9 thru UB-44).

(3) Place the Elevator Trim System Preflight Check Procedure, shown in Attachment 1 of this AD, in the Limitations Section of the FAA Approved Flight Manual for the Models 65-A90, B90, C90, E90, and 200T/200CT airplanes; and the Limitations Section of the Pilot's Operating Handbook and the FAA Approved Airplane Flight Manual for the Models C90, C90A, F90, 200/200C, B200/B200C, B200T, B200CT, 300, and 1900/1900C airplanes.

(c) Prior to May 15, 1987, modify the elevator trim system on all airplanes which have not complied with the requirements of paragraph (a) of this AD, in accordance with Part III of Beechcraft Service Bulletin No. 2028, Rev. III, dated February 1987.

(d) Compliance with paragraph (b) of this AD is no longer necessary after the modification required in paragraph (c) of this AD is accomplished.

(e) Airplanes may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished.

(f) An equivalent means of compliance with this AD may be used, if approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas 67209; Telephone (316) 946-4400.

All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Beechcraft Aero and Aviation Centers or Beech Aircraft Corporation, Commercial Service Department 52, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine copies of the document(s) referred to herein at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This AD supersedes AD 86-20-03, Amendment 39-5413.

This amendment becomes effective on April 14, 1987, to all persons except those to whom it has already been made effective by priority letter from the FAA dated February 23, 1987, and is identified as AD 87-04-24.

ATTACHMENT 1 - 87-04-24

OPERATING LIMITATION:

The Elevator Trim System Preflight check procedure, as defined below, must be conducted prior to each flight.

To verify that the elevator trim cable is not fouled or disengaged from the cable drum, the following Elevator Trim System Preflight Check is required prior to each flight of the Beech Model 65-A90, B90, C90, C90A, E90, F90, 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, 300, 1900 and 1900C airplanes:

COCKPIT

1. Control Locks - REMOVE

2. Elevator Trim:

a. All airplanes except 1900/1900C - SET TO "O" UNITS

b. 1900/1900C airplanes - SET TWO UNITS NOSE UP CAUTION

The elevator trim system must not be forced past the limits which are indicated on the elevator trim indicator scale either manually, electrically (except Model 300) or by action of the autopilot (except Model 300).

TAIL SECTION

1. Elevator Trim Tab

a. VERIFY "O" (NEUTRAL) POSITION

2. On Model 65-A90, B90, C90, C90A and E90 airplanes, the elevator trim tab "O" (neutral) position is determined by observing that the alignment marks on the elevator trim tab pushrods align with the alignment marks on the elevator (See Figure 1 or 2 below), when the elevator is resting against the downstops.

3. On Model F90, 200 Series, 300 and 1900/1900C airplanes, the elevator trim tab "O" (neutral) position is determined by observing that the trailing edge of the elevator trim tab aligns with the trailing edge of the elevator, when the elevator, when the elevator is resting against the downstops.

WARNING

The above Preflight Inspection check MUST be repeated prior to take-off if the elevator trim is allowed to reach limit travel at any time prior to take-off as a result of MANUAL, ELECTRICAL (except Model 300) OR AUTOPILOT (except Model 300) OPERATION of the trim system.



FOOTER: