AD 80-04-07

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AD Number:
80-04-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Beech Model 60, A60 and B60 Airplanes
Subject:
Outboard Wing Panel Nuts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/16/1980
Make:
Textron Aviation Inc.
Model:
60 | A60 | B60
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Superseded AD: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Superseded By: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: 80-04-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3694

AD NUMBER:   80-04-07

SUBJECT HEADING:   Airworthiness Directives; Beech Model 60, A60 and B60 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 16, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-04-07 BEECH: Amendment 39-3694. Applies to the following airplanes certificated in all categories:

Model	Serial Number
60	P-4 through P-122 and P-124 through P-126
A60	P-123, P-127 through P-246
B60	P-247 through P-519, P-521 and P-522

Compliance: Required as indicated unless already accomplished in accordance with the corresponding emergency AD dated November 30, 1979.

To assure structural integrity of the attachment of the left and right outboard wing panel to the wing center section, even though AD 76-25-04 and the emergency AD dated November 24, 1979, both on this same subject, have already been complied with, accomplish the following:

A) Prior to the next flight:

1. On airplanes having Serial Numbers P-486 through P-519, P-521 and P- 522:

a. Remove, and prior to approving the airplane for return to service reinstall, the wing attach fitting cover plates located on the bottom of the left and right wing at the front spar inboard of the engine nacelles.

b. Using a light and mirror, visually inspect the Part Number 42FLW-1414 nut, located in the left and right outer wing panel to wing center section attach fittings on the wing front spar lower cap, for splitting or cracking. Replace any cracked or split nuts, in accordance with instructions in Paragraph A.2. of this Airworthiness Directive (AD), with new Part Number FN22M-1414, FN22-1414 or 72789-1414 nuts obtainable from Beech Aircraft Corporation or accomplish Paragraph A.2.a., b., c. and d. below.

NOTE: A crack, if existing, will most likely be oriented parallel to the nut wrenching serrations.

c. Review the airplane maintenance records and, if there is any entry showing that the left or right outboard wing panel has been removed or replaced, or that the Part Number 42FLW-1414 nuts have been loosened, replace the nuts in accordance with Paragraph A.2.a., b., c. and d. of this AD.

d. Unless accomplished during compliance with Paragraphs A.1.b. or A.1.c. above, within (1) 200 hours time-in-service or, (2) 6 months after the date of the issuance of this AD, whichever occurs first:

Comply with Paragraphs A.2.a., b., c. and d. of this AD as set forth below.

2. On airplanes having Serial Numbers P-4 through P-485:

a. Remove, and prior to approving the airplane for return to service reinstall, the wing attach fitting cover plates located on the bottom of left and right wing at the front spar inboard of the engine nacelles.

b. Assure that the radii on the outer circumference of the washers, next (adjacent) to the wing attachment fitting in the outer wing panel and in the wing center section, are facing (adjacent to) the radius in the end of the wing fitting recess. If a radius is not oriented as shown in Figure 1 of this AD, contact Beech Service Department at telephone number (316) 681-7601 or 681-8495 for rework disposition. If oriented properly, proceed to Paragraph A.2.c.

c. Remove the 42FLW-1414 nut, 60-100019 washer, and 60- 100024 spacer and return to Beech Aircraft Corporation with airplane identification. Inspect the surface of the outboard wing attach fitting for condition in the washer seat area. If any scoring or coining of the fitting is noted, contact Beech Aircraft Corporation Service Department (316) 681- 7601 or 681-8495 for rework disposition. If the condition of the fitting is satisfactory, clean and lubricate the bolt threads with General Electric G322L Silicone Lubricant or Locktite Corporation Anti-Seize Compound per MIL-A-907 and install torque indicating washer assembly P/N 61475- 14-43.5, and nut P/N FN22-1414, FN22M-1414, or 72789-1414 per Figure 1. While the airplane is on jacks, tighten the nut until the inner center ring washer compresses so that the center outer ring washer will no longer turn with finger pressure. Torque wrench reading not necessary.

Caution: Lubrication of threads not permitted at any other wing to fuselage attachments.

d. Between 95 and 105 hours' time-in-service after nuts are installed in accordance with Paragraph A.2.c of this AD, check the center outer ring of the washer with finger pressure. If the ring turns, place the airplane on jacks and tighten the nut until the ring no longer turns. Bolts and nuts are thereafter reusable, but do not reuse the P/N 61475- 14-43.5 washer assembly after being loaded.

B) Any affected airplanes which complied with Emergency Airworthiness Directive Letter dated November 24, 1979, by (1) satisfactory completion of inspections required by Paragraph A.2.a. and A.2.b. of that AD without installation of new nuts or, (2) installation of new Part Number FN22M-1414, FN22-1414 or 72789-1414 nuts without installation of the P/N 61475-14-43.5 preload indicating torque washer assembly and anti-seize compound must comply with Paragraph A.2.a., b., c. and d. of this AD within the next 200 hours in service, or 6 months after the date of issuance of this AD, whichever occurs first.

Any new Part Number FN22M-1414, FN22-1414 or 72789-1414 nuts, installed during compliance with the November 24, 1979, emergency AD on this same subject may be reused when complying with this paragraph of this AD.

C) Within 24 hours after finding any cracking or splitting of a nut or any discrepancy concerning washer position, report same to Federal Aviation Administration (FAA) at telephone (316) 942-4219. Collect calls will be accepted for these reports. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) Failure to comply with this paragraph subjects owners/operators to agency enforcement action.

D) A special flight permit, in accordance with FAR 21.197, for one flight up to 5 hours duration is permitted provided the visual inspection set forth in Paragraph A.1.b. of this AD is accomplished prior to issuance of the permit.

E) 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.

Beech Aircraft Corporation's Executive Airplane Service Communique Number 46 dated November 27, 1979, and Beechcraft Service Instructions No. 1100 pertain to this matter.

This AD supersedes AD 76-25-04, Amendment 39-2787.

This Amendment 39-3694 becomes effective on February 16, 1980, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated November 30, 1979.




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