AD 80-07-05

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AD Number:
80-07-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Beech Model 99, 99A, B99, A100-1, 200, A200, A200C, 200C, 200T, F90, H90,...Show more
Subject:
Bolt and Nut, Wing Section
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/03/1980
Make:
Textron Aviation Inc.
Model:
200 | 200C | 200T | 99 | 99A | A100-1 (U-21J) | A200 (C-12A) | A200 (C-12C) | A200C (UC-12B) | B99 |...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Superseded AD: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Superseded By: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: 80-07-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3728

AD NUMBER:   80-07-05

SUBJECT HEADING:   Airworthiness Directives; Beech Model 99, 99A, B99, A100-1, 200, A200, A200C, 200C, 200T, F90, H90, T-34C, T-34C-1 and 34C Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 3, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-07-05 BEECH: Amendment 39-3728. Applies to the following airplanes regardless of the category or categories of airworthiness certification:


BEECH MODEL	SERIAL NUMBERS
99	U-40, U-55, U-67, U-73, U-87, U-90
99A	U-96, U-126
B99	U-152, U-153
A100-1 (Military RU-21J)	BB-3 through BB-5
200 (Military RU-21J)	BB-2, BB-6 through BB-599
BB-601 through BB-606
BB-608 through BB-613
BB-620
A200 (Military C-12A, C-12C)	BC-1 through BC-75
BD-1 through BD-30
A200C (Military UC-12B)	BJ-1 through BJ-8
200C	BL-1 through BL-5
200T	BT-1 through BT-10
F90	LA-2 through LA-15, LA-22
LA-23, LA-25, LA-26, LA-28
H90 (Military T-44A)	LL-1 through LL-61
T-34C	GL-2
GL-4 through GL-163
T-34C-1	GM-1 through GM-13
GM-15 through GM-71
GM-78
34C	GP-1 through GP-6

COMPLIANCE: Required as indicated.

In order to assure integrity of attachments of the outer wing panels to the wing center section, accomplish the following for the left and for the right sides of each affected airplane:

A) Prior to the next flight unless already accomplished for compliance with the corresponding emergency AD transmitted by letter dated February 11, 1980 (for Models 99 and 200 Series) or a communique or service instruction specified by Table 1, below, accomplish the following at the lower forward wing attachment:

NOTE: Hereafter in this AD, the words, "barrel nut assembly", "washer assembly", and "bolt" mean the parts and part numbers for an airplane as specified by Table 1, below:

TABLE 1
Airplane Model (Read downward)
99, 99A, B99
	
200, A200, A200C,
	
F90, H90
	
T-34C-1

	
200C, 200T, A100-1
		
34C, T-34C

Barrel Nut Assembly
RMLH7940T-144
	
RMLH7940T-162
	
RMLH7940T-144
	
RMLH7940T-162


or
113LH7940T-144
	
or
113LH7940T-162
	
or
113LH7940T-144
	
or
113LH7940T-162

Washer Assembly
90-380019-1
	
73757-16-58.6
	
73757-14-43.5
	
73757-16-58.6

		
or
90-380019-1
	

Bolt
LWB22-14-46
	
LWB22-16-44
	
LWB22-14-46
	
NAS636-40

	
or
VEP220121-16V44
	
or
VEP220121-14V46
	
or
NAS636-H40

Torque, Foot-Pounds, per Paragraph A)11. below
280
	
300
	
280
	
50-100 on jacks

			
then
375 on wheels

Beechcraft Safety Communique or Service Instructions
200-51A
	
200-51A, 200-52
	
200-52 or
	
200-51A, or


or 200-52
	
or C-12-0053
	
T-44A-0038
	
T-34C-0140, or

			
T-34C-1-0074

Part Number or Applicable Beech Maintenance Manual or Drawing

Drawing 99-4023
	
101-590010-19,
	
(90-590012-13+
	
104-590025-5,

	
92-37443-1,
	
Suppl. 92-37056)
	
92-37867,

	
or 92-37443-2
	
or 109-590010-19
	
or 98-37986
1. Remove the bolt, washer assembly and barrel nut assembly from the lower forward wing attachment. After turning the bolt out of the barrel nut assembly, remove the bolt by hand without using any tool. Reposition the wing as necessary for such removal.

a. Throughout all action required by this AD, keep parts of each washer assembly together so that parts of one assembly are not intermingled with parts of another assembly.

b. Thoroughly clean all removed parts with naphtha or methyl ethyl ketone (MEK), using a bristle brush as necessary. Prior to each subsequently specified action (until lubricant is applied) ascertain that the parts are clean, repeating the cleaning process whenever this is necessary.

2. Disassemble the barrel nut assembly sufficiently to separate the cradle from the threaded body of the nut.

NOTE: Hereafter in this AD, the word "nut" means the threaded body in the barrel nut assembly.

3. Visually inspect the bolt, nut and cradle for reddish rust. Do not classify copper residue over cadmium plating as rust.

4. Using a 10X magnifying glass, visually inspect each bolt and nut for a pit or a crack in steel (not plating) material. For the bolt, pay particular attention to the fillet and shank, including threads. For the nut, pay particular attention to the chamfer (that faces the bolt head when installed) and perceptible threads adjacent to this chamfer.

NOTE: Refer to Paragraph A)7., below.

5. Bake the bolt and nut continuously for 23 hours at 350 degrees to 400 degrees Fahrenheit and cool in still air.

6. After accomplishment of Paragraph A)5., above, use a magnetic particle method of Advisory Circular AC43.13-1A to inspect the bolt and nut for a crack, paying particular attention to locations specified in Paragraph A)4., above. For the bolt, use a fluorescent particle method with approximately 6000 ampere-turns in a coil to produce longitudinal magnetization in the bolt. For the nut, use any magnetic particle method with 500 to 700 amperes through a central conductor of at least 0.6-inch diameter through two nuts to produce circular magnetization. Demagnetize the bolt and nut after the above inspection.

7. Replace each rusted, pitted and/or cracked nut and bolt and each rusted cradle with a new part of a P/N shown by Table 1. Obtain the new part(s) from Beech Aircraft Corporation. Reassemble the barrel nut assembly. (Baking and field inspection of these new parts are not necessary.) (Caution: Do not recadmium plate any of the wing attachment components.)

8. Clean the bore and recessed washer/cradle seat area of the outboard and inboard wing fittings with naphtha or methyl ethyl ketone ("MEK"). Visually inspect these areas for burrs, gouges and coining. If any defect is found, contact Beech Aircraft Service Department, 9709 East Central, Wichita, Kansas 67201, telephone (316) 681-7261, 7278, 8365, or 7656, for rework disposition.

9. Treat the bore and recessed washer/cradle seat areas of the inboard and outboard wing fittings with Alodine 1200 or 1201. Allow the alodine coating to dry for 5 minutes. Wash the coating with water and blow dry with air without wiping.

10. Coat the Alodined areas of the wing fittings, the fillet, shank, and threaded portion of the bolt, the cradle, and all portions of the nut with either clean MIL-C-16173, Grade 2 compound or clean General Electric G322L Versilube. (General Electric Company, Silicone Products Department, Waterford, New York 12188, can help locate a source of G322L Versilube.)

11. Install the nut assembly along with the bolt and washer assembly. For this, except as noted below, use procedures in the Beech Maintenance Manual, or the Beech Drawing that is specified for an airplane by Table 1, above.

a. Reuse of the washer assembly is authorized for compliance with this AD.

b. Position the wing as necessary to allow the bolt to be inserted into the fittings by hand without the use of any tool.

c. Use the standard procedure for tightening the bolt whenever a new washer assembly has been used.

d. If a used washer assembly is being installed, tighten with measured torque as specified by Table 1, above, while the necessary correction for any adapter is made and while the socket does not bear against the fitting of the wing center section. Then, test the outer center ring of the washer assembly with a pin inserted in the test hole, and contact Beech Aircraft Service Department (See Paragraph A)8., above) if the ring rotates.

e. Coat the entire portion of the bolt that projects beyond the nut assembly with material (MIL-C-16173 or Versilube) used for compliance with Paragraph A)10., above.

B) Prior to approving the airplane for return to service, devise a procedure to assure that the MIL-C-16173 or Versilube used per Paragraph A), above, is not removed or destroyed while the airplane is in service or being washed. If necessary to accomplish this, fabricate and install appropriate markings and placarding.

C) Between 90 and 110 hours time-in-service after accomplishment of action specified by Paragraph A) of this AD, check bolt tightness, using the same procedure that was used for accomplishment Paragraph A)11.c or A)11.d, above.

D) Within 3 days after replacing a part in accordance with Paragraph A)7., above, submit a written report to the Federal Aviation Administration via an FAA M or D Report (FAA Form 8330-2) or a letter to the office specified in Paragraph F), below, and send the replaced part(s) to Beech Aircraft Corporation.

E) A special flight permit in accordance with Federal Aviation Regulation 21.197 for a flight not exceeding a total of ten hours duration is permitted in order to accomplish this AD. The nearest FAA Flight Standards District Office may be contacted to obtain a telegraphic special flight permit.

F) Any equivalent method of compliance with this AD must be approved by the Chief, Wichita Engineering and Manufacturing District Office, Federal Aviation Administration, Room 238, Terminal Building, Mid-Continent Airport, Wichita, Kansas 67209, telephone (316) 942-4285.

This amendment becomes effective on April 3, 1980, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated February 11, 1980.

FOOTER: