AD 85-22-05
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | 100 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 200 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 200C | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 200CT | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 200T | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 50 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 60 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-80 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-88 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-90 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-A80 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-A80-8800 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-A90 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-A90-1 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-A90-2 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-A90-3 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-A90-4 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 65-B80 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 70 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 99 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 99A | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | 99A (FACH) | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A100 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A100-1 (U-21J) | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A100A | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A200 (C-12A) | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A200 (C-12C) | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A200C (UC-12B) | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A200CT (C-12D) | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A200CT (C-12F) | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A200CT (FWC-12D) | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A60 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A65 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A65-8200 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A99 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | A99A | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | B100 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | B200 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | B200C | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | B200C (C-12F) | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | B50 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | B60 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | B90 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | B99 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | C50 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | C90 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | C99 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | D50 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | D50A | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | D50B | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | D50C | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | D50E | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | D50E-5990 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | E50 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | E90 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | F50 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | F90 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | G50 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | H50 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | H90 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | J50 | Airworthiness Directives; Beech Models Listed in Table I Below |
| aircraft | Textron Aviation Inc. | T-34C | Airworthiness Directives; Beech Models Listed in Table I Below |
Unsafe Condition
Nuts and Bolts Replacement
Federal Register Abstract
Nuts and Bolts Replacement
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_85-22-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 85-22-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Beech Models Listed in Table I Below Subject: Nuts and Bolts Replacement Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/12/1985 Make: Textron Aviation Inc. Model: 100 | 200 | 200C | 200CT | 200T | 50 | 60 | 65 | 65-80 | 65-88 | 65-90 | 65-A80 | 65-A80-8800 | 65-A...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: 85-22-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5146 AD NUMBER: 85-22-05 SUBJECT HEADING: Airworthiness Directives; Beech Models Listed in Table I Below ACTION: SUMMARY: DATES: Effective on November 12, 1985. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 85-22-05 BEECH: Amendment 39-5146. Applies to Beech airplanes listed in Table I below, certificated in any category, upon accrual of five years in service. This AD does not apply to those airplanes in which bolts and nuts made of Inconel have been installed in the wing attachment joints that are specified in Table I below. 85-22-05 TABLE I BEECH MODEL (MILITARY MODEL) SERIAL NUMBER JOINTS (1) INSTRUCTION (2) 34C GP-1 and up LF,UF,UR,LR T-34C-1-0083 T-34C GL-1 and up LF,UF,UR,LR T-34C-0158R2 T-34C-1 GM-1 and up LF,UF,UR,LR T-34C-1-0083 50 H-1 thru H-11 LF* P/N 98-39006 50 (L-23A,U-8A) LH-1 thru LH-55 LF* See Note 3a B50 CH-12 thru CH-110 LF* P/N 98-39006 B50 (L-23B) LH-56 thru LH-95 LF* See Note 3b C50 CH-111 thru CH-360 LF* P/N 98-39006 D50 (L-23E, L-23G) DH-1 thru DH-154 LF* P/N 98-39006 D50A, D50B, D50C DH-155 thru DH-300 LF* P/N 98-39006 D50E, D50E-5990 DH-301 thru DH-347 LF* P/N 98-39006 E50 EH-1 thru EH-70 LF* P/N 98-39006 E50 (L-23D, U-8D) LH-96 and up LF* See Note 3b E50 (RL-23D, RU-8D) RLH-1 and up LF* See Note 3b E50 (RL-23D, RU-8D) LHC-1 and up LF* See Note 3b E50 (RL-23D, RU-8D) LHD-1 and up LF* See Note 3b E50 (RL-23D, RU-8D) RLHE-1 and RLHE-2 LF* See Note 3b E50 (RL-23D, RU-8D) LHE-3 and up LF* See Note 3b F50 FH-71 thru FH-96 LF* P/N 98-39006 G50 GH-94 thru GH-119 LF* P/N 98-39006 H50 HH-120 thru HH-149 LF* P/N 98-39006 J50 JH-150 thru JH-176 LF* P/N 98-39006 60, A60, B60 P-4 and up LF, UF, LR P/N 60-590001- 25A13 65 LC-1 thru LC-239 LF* P/N 98-39006 65 (L-23F, U-8F) L-1 thru L-6 LF* See Note 3b 65 (L-23F, U-8F) LF-7 and up LF* See Note 3b A65, A65-8200 LC-240 thru LC-335 LF* P/N 98-39006 65-80, 65-A80, 65-A80-8800 LD-1 thru LD-269 LF* P/N 98-39006 65-B80 LD-270 and up LF* P/N 98-39006 65-88 LP-1 thru LP-47 LF* P/N 98-39006 65-A90-1 (U-21A, RU-21A, RU-21D, JU-21A, U-21G, RU-21H) LM-1 and up LF* See Note 3c 65-A90-2 (RU-21B) LS-1 and up LF* See Note 3c 65-A90-3 (RU-21C) LT-1 and up LF* See Note 3c 65-A90-4 (RU-21E, RU-21H) LU-1 and up LF* See Note 3c 70 LB-1 thru LB-35 LF* P/N 98-39006 65-90, 65-A90, B90, C90 LJ-1 thru LJ-993 LJ-995 thru LJ-1007 LJ-1009 thru LJ-1034 LJ-1037 & LJ-1039 thru LJ-1044 LF* LF* LF* LF* LF* P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 E90 LW-1 thru LW-347 LF* P/N 98-39006 F90 LA-2 thru LA-90 LA-92 thru LA-156 LA-158 thru LA-169 LA-171 thru LA-173 LA-175 thru LA-182 LA-185, LA-187 LA-189 thru LA-191 LA-193 thru LA-196 and LA-199 LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 H-90 (T-44A) LL-1 thru LL-18 LL-20 thru LL-40 LL-42 thru LL-48 LL-50 thru LL-61 LF LF LF LF T-44A-0049R1 T-44A-0049R1 T-44A-0049R1 T-44A-0049R1 99, 99A, 99A (FACH) U-1 thru U-49 and LF* P/N 98-39006 A99, A99A, & B99 U-51 thru U-164 LF* P/N 98-39006 C99 U-50 and U-165 thru U-179 U-181 thru U-184 U-186 thru U-192 U-194 thru U-196 LF,UF LF,UF LF,UF LF,UF LF,UF P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 100, A100 & A100A B-1 thru B-247 LF* P/N 98-39006 B100 BE-2 thru BE-131, and BE-135 LF* LF* P/N 98-39006 P/N 98-39006 A100-1 BB-2 thru BB-342 LF,UF P/N 98-39006 (RU-21J), 200, BB344 thru BB-983 LF,UF P/N 98-39006 and B200 BB-985 thru BB-1038 LF,UF P/N 98-39006 B200 BB-1040 thru BB-1045 BB-1047 thru BB-1049 BB-1053 thru BB-1078 & BB-1080 LF,UF LF,UF LF,UF LF,UF P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 200C, B200C BL-1 thru BL-51 LF,UF P/N 98-39006 (C-12F) BL-53, BL-55 LF,UF P/N 98-39006 200 CT BN-1 LF,UF P/N 98-39006 200 T BT-1 thru BT-22 LF,UF P/N 98-39006 A200 (C-12A, C-12C) BC-1 thru BC-75 BD-1 thru BD-30 LF,UF LF,UF P/N 98-39006 P/N 98-39006 A200C (UC-12B) BJ-1 thru BJ-47 LF,UF P/N 98-39006 A200CT (C-12D,FWC-12D) BP-1 thru BP-27 LF,UF P/N 98-39006 (*-See Note 4) NOTE 1: Wing attachment joints, on left and right sides of each airplane, are abbreviated as: LF=lower forward, UF=upper forward, UR=upper rear, LR=lower rear. NOTE 2: T-34C-1-0083-1, T-34C-0158 Rev. 2, and T-44A-0049 Rev. 1 are Beech Service Instructions. Cited Beech Manuals, and their earliest applicable revision dates are: PART NUMBER NAME DATE 60-590001-25 Maintenance Manual June 13, 1984 98-39006 Structural Inspection and Repair Manual December 20, 1984 NOTE 3: Apply the following portions of P/N 98-39006 manual even though applicability to military models is not shown within the P/N 98-39006 manual: NOTE MANUAL SECTION REFERENCE FIGURE BOLT P/N NUT P/N 3a 57-10-00 209 NAS495-14-27 EB-144 3b 57-11-00 210 MS20014-29 EB-144 3c 57-13-00 212 LWB-14-32 FN22-1414 Compliance: Required initially, upon accrual of five years after first airworthiness certification or within 60 days after the effective date of this AD (whichever is later), unless already accomplished, and thereafter at intervals which do not exceed five years. To assure structural integrity of attachments of outer wing panels to the wing center section, use procedures in instructions identified in Table I of this AD to accomplish the following at each wing attachment joint that is specified for a particular airplane by Table I of this AD: (a) Remove each steel nut and each steel tension bolt. Use visual and magnetic particle methods to inspect the bolt and nut for cracking and corrosion in parent steel, and replace each bolt and nut found cracked or corroded. NOTE 4: In lower forward joints that are asterisked in Table I of this AD, while bolts are removed for accomplishment of Paragraph (a), above, it is recommended that inboard and outboard fittings be inspected, by a fluorescent penetrant method, for fatigue cracks in washer face areas of the fittings. For some of the asterisked joints, inspections of fittings are required by other AD's, but inspections of fittings are not required by this AD. (b) During reassembly of each joint, coat the bolt, nut, and adjacent parts with MIL- C-16173 Grade 2 corrosion preventative compound. (c) Within the next 150 hours of flight time, check joint tightness, and tighten as necessary. (d) Inject MIL-C-16173 Grade 2 corrosion preventative compound into a lubrication fitting on each barrel nut, (wherever a barrel nut is used) when joint tightness is checked per Paragraph (c), above, and thereafter at intervals which do not exceed one year. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (f) For destructive or nondestructive examination and any specified return, each nut and each bolt that is replaced in response to this AD must be identified with the related years in service, joint, and airplane serial number and sent to FAA/AVN-112, Room 203, Aviation Records Building, Mike Monroney Aeronautical Center, 6500 South MacArthur Boulevard, Post Office Box 26460, Oklahoma City, Oklahoma 73125. Parts so sent will be destroyed if return to a specified address is not requested. Reporting requirements approved by OMB pursuant to clearance No. 2120 0056. (g) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Wichita Aircraft Certification Office, Room 100, 1801 Airport Road, Wichita, Kansas 67209; telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beechcraft Aero and Aviation Centers; Beech Aircraft Corporation, 9709 East Central, Post Office Box 85, Wichita, Kansas 67201, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on November 12, 1985. FOOTER:
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AD Final Rules - DRS_85-22-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 85-22-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Beech Models Listed in Table I Below Subject: Nuts and Bolts Replacement Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/12/1985 Make: Textron Aviation Inc. Model: 100 | 200 | 200C | 200CT | 200T | 50 | 60 | 65 | 65-80 | 65-88 | 65-90 | 65-A80 | 65-A80-8800 | 65-A...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: 85-22-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5146 AD NUMBER: 85-22-05 SUBJECT HEADING: Airworthiness Directives; Beech Models Listed in Table I Below ACTION: SUMMARY: DATES: Effective on November 12, 1985. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 85-22-05 BEECH: Amendment 39-5146. Applies to Beech airplanes listed in Table I below, certificated in any category, upon accrual of five years in service. This AD does not apply to those airplanes in which bolts and nuts made of Inconel have been installed in the wing attachment joints that are specified in Table I below. 85-22-05 TABLE I BEECH MODEL (MILITARY MODEL) SERIAL NUMBER JOINTS (1) INSTRUCTION (2) 34C GP-1 and up LF,UF,UR,LR T-34C-1-0083 T-34C GL-1 and up LF,UF,UR,LR T-34C-0158R2 T-34C-1 GM-1 and up LF,UF,UR,LR T-34C-1-0083 50 H-1 thru H-11 LF* P/N 98-39006 50 (L-23A,U-8A) LH-1 thru LH-55 LF* See Note 3a B50 CH-12 thru CH-110 LF* P/N 98-39006 B50 (L-23B) LH-56 thru LH-95 LF* See Note 3b C50 CH-111 thru CH-360 LF* P/N 98-39006 D50 (L-23E, L-23G) DH-1 thru DH-154 LF* P/N 98-39006 D50A, D50B, D50C DH-155 thru DH-300 LF* P/N 98-39006 D50E, D50E-5990 DH-301 thru DH-347 LF* P/N 98-39006 E50 EH-1 thru EH-70 LF* P/N 98-39006 E50 (L-23D, U-8D) LH-96 and up LF* See Note 3b E50 (RL-23D, RU-8D) RLH-1 and up LF* See Note 3b E50 (RL-23D, RU-8D) LHC-1 and up LF* See Note 3b E50 (RL-23D, RU-8D) LHD-1 and up LF* See Note 3b E50 (RL-23D, RU-8D) RLHE-1 and RLHE-2 LF* See Note 3b E50 (RL-23D, RU-8D) LHE-3 and up LF* See Note 3b F50 FH-71 thru FH-96 LF* P/N 98-39006 G50 GH-94 thru GH-119 LF* P/N 98-39006 H50 HH-120 thru HH-149 LF* P/N 98-39006 J50 JH-150 thru JH-176 LF* P/N 98-39006 60, A60, B60 P-4 and up LF, UF, LR P/N 60-590001- 25A13 65 LC-1 thru LC-239 LF* P/N 98-39006 65 (L-23F, U-8F) L-1 thru L-6 LF* See Note 3b 65 (L-23F, U-8F) LF-7 and up LF* See Note 3b A65, A65-8200 LC-240 thru LC-335 LF* P/N 98-39006 65-80, 65-A80, 65-A80-8800 LD-1 thru LD-269 LF* P/N 98-39006 65-B80 LD-270 and up LF* P/N 98-39006 65-88 LP-1 thru LP-47 LF* P/N 98-39006 65-A90-1 (U-21A, RU-21A, RU-21D, JU-21A, U-21G, RU-21H) LM-1 and up LF* See Note 3c 65-A90-2 (RU-21B) LS-1 and up LF* See Note 3c 65-A90-3 (RU-21C) LT-1 and up LF* See Note 3c 65-A90-4 (RU-21E, RU-21H) LU-1 and up LF* See Note 3c 70 LB-1 thru LB-35 LF* P/N 98-39006 65-90, 65-A90, B90, C90 LJ-1 thru LJ-993 LJ-995 thru LJ-1007 LJ-1009 thru LJ-1034 LJ-1037 & LJ-1039 thru LJ-1044 LF* LF* LF* LF* LF* P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 E90 LW-1 thru LW-347 LF* P/N 98-39006 F90 LA-2 thru LA-90 LA-92 thru LA-156 LA-158 thru LA-169 LA-171 thru LA-173 LA-175 thru LA-182 LA-185, LA-187 LA-189 thru LA-191 LA-193 thru LA-196 and LA-199 LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR LF,UR,LR P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 H-90 (T-44A) LL-1 thru LL-18 LL-20 thru LL-40 LL-42 thru LL-48 LL-50 thru LL-61 LF LF LF LF T-44A-0049R1 T-44A-0049R1 T-44A-0049R1 T-44A-0049R1 99, 99A, 99A (FACH) U-1 thru U-49 and LF* P/N 98-39006 A99, A99A, & B99 U-51 thru U-164 LF* P/N 98-39006 C99 U-50 and U-165 thru U-179 U-181 thru U-184 U-186 thru U-192 U-194 thru U-196 LF,UF LF,UF LF,UF LF,UF LF,UF P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 100, A100 & A100A B-1 thru B-247 LF* P/N 98-39006 B100 BE-2 thru BE-131, and BE-135 LF* LF* P/N 98-39006 P/N 98-39006 A100-1 BB-2 thru BB-342 LF,UF P/N 98-39006 (RU-21J), 200, BB344 thru BB-983 LF,UF P/N 98-39006 and B200 BB-985 thru BB-1038 LF,UF P/N 98-39006 B200 BB-1040 thru BB-1045 BB-1047 thru BB-1049 BB-1053 thru BB-1078 & BB-1080 LF,UF LF,UF LF,UF LF,UF P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 200C, B200C BL-1 thru BL-51 LF,UF P/N 98-39006 (C-12F) BL-53, BL-55 LF,UF P/N 98-39006 200 CT BN-1 LF,UF P/N 98-39006 200 T BT-1 thru BT-22 LF,UF P/N 98-39006 A200 (C-12A, C-12C) BC-1 thru BC-75 BD-1 thru BD-30 LF,UF LF,UF P/N 98-39006 P/N 98-39006 A200C (UC-12B) BJ-1 thru BJ-47 LF,UF P/N 98-39006 A200CT (C-12D,FWC-12D) BP-1 thru BP-27 LF,UF P/N 98-39006 (*-See Note 4) NOTE 1: Wing attachment joints, on left and right sides of each airplane, are abbreviated as: LF=lower forward, UF=upper forward, UR=upper rear, LR=lower rear. NOTE 2: T-34C-1-0083-1, T-34C-0158 Rev. 2, and T-44A-0049 Rev. 1 are Beech Service Instructions. Cited Beech Manuals, and their earliest applicable revision dates are: PART NUMBER NAME DATE 60-590001-25 Maintenance Manual June 13, 1984 98-39006 Structural Inspection and Repair Manual December 20, 1984 NOTE 3: Apply the following portions of P/N 98-39006 manual even though applicability to military models is not shown within the P/N 98-39006 manual: NOTE MANUAL SECTION REFERENCE FIGURE BOLT P/N NUT P/N 3a 57-10-00 209 NAS495-14-27 EB-144 3b 57-11-00 210 MS20014-29 EB-144 3c 57-13-00 212 LWB-14-32 FN22-1414 Compliance: Required initially, upon accrual of five years after first airworthiness certification or within 60 days after the effective date of this AD (whichever is later), unless already accomplished, and thereafter at intervals which do not exceed five years. To assure structural integrity of attachments of outer wing panels to the wing center section, use procedures in instructions identified in Table I of this AD to accomplish the following at each wing attachment joint that is specified for a particular airplane by Table I of this AD: (a) Remove each steel nut and each steel tension bolt. Use visual and magnetic particle methods to inspect the bolt and nut for cracking and corrosion in parent steel, and replace each bolt and nut found cracked or corroded. NOTE 4: In lower forward joints that are asterisked in Table I of this AD, while bolts are removed for accomplishment of Paragraph (a), above, it is recommended that inboard and outboard fittings be inspected, by a fluorescent penetrant method, for fatigue cracks in washer face areas of the fittings. For some of the asterisked joints, inspections of fittings are required by other AD's, but inspections of fittings are not required by this AD. (b) During reassembly of each joint, coat the bolt, nut, and adjacent parts with MIL- C-16173 Grade 2 corrosion preventative compound. (c) Within the next 150 hours of flight time, check joint tightness, and tighten as necessary. (d) Inject MIL-C-16173 Grade 2 corrosion preventative compound into a lubrication fitting on each barrel nut, (wherever a barrel nut is used) when joint tightness is checked per Paragraph (c), above, and thereafter at intervals which do not exceed one year. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (f) For destructive or nondestructive examination and any specified return, each nut and each bolt that is replaced in response to this AD must be identified with the related years in service, joint, and airplane serial number and sent to FAA/AVN-112, Room 203, Aviation Records Building, Mike Monroney Aeronautical Center, 6500 South MacArthur Boulevard, Post Office Box 26460, Oklahoma City, Oklahoma 73125. Parts so sent will be destroyed if return to a specified address is not requested. Reporting requirements approved by OMB pursuant to clearance No. 2120 0056. (g) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Wichita Aircraft Certification Office, Room 100, 1801 Airport Road, Wichita, Kansas 67209; telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beechcraft Aero and Aviation Centers; Beech Aircraft Corporation, 9709 East Central, Post Office Box 85, Wichita, Kansas 67201, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on November 12, 1985. FOOTER:
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