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
57-11-00210
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.