AD 80-22-01

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AD Number:
80-22-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes
Subject:
Wing Skin And Spar Cap
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/23/1980
Make:
The Boeing Company
Model:
DC-8-11 | DC-8-12 | DC-8-21 | DC-8-31 | DC-8-32 | DC-8-33 | DC-8-41 | DC-8-42 | DC-8-43 | DC-8-51 | ...Show more
Product Type:
Aircraft
Product Subtype:
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Superseded AD: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Superseded By: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: 80-22-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3946

AD NUMBER:   80-22-01

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective October 23, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-22-01 MCDONNELL DOUGLAS: Amendment 39-3946. Applies to Model DC-8 series airplanes with 20,000 or more hours time in service, certificated in all categories.

Compliance required as indicated unless already accomplished. To prevent crack growth which could result in structural failure of the wing lower skin and rear spar lower cap, accomplish the following:

(a) Visually inspect the lower inboard aft wing skin panels and aft tang of the rear spar cap in the vicinity of the dihedral break at wing station Xcw=69.500 per the Phase 1 accomplishment instructions (Part 2) of McDonnell Douglas Service Bulletin 57-88 dated January 23, 1980, (hereinafter referred to as SB 57-88) within the times specified below:

For airplanes with total hours time
in service on or after the effective
date of this AD.
	
Inspect within additional
hours time in service from
the effective date of this AD.



20,000 to 24,999
	
900


25,000 to 29,999
	
700


30,000 to 34,999
	
500


35,000 and over
	
300

(b) Modify Clip P/N 5649893-47 (Left Side) and -48 (Right Side) per SB57-88, Part 2, Accomplishment Instructions, Paragraph G within the compliance schedule specified in Paragraph (a) of this AD.

(c) Precoin ream the six holes in lower wing skin identified in SB57-88, Part 2.H per instructions of SB57-88, Part 2.H, Condition II, Paragraph 1, within the compliance schedule specified in Paragraph (a) of this AD.

(d) Ream five attachment holes identified in SB57-88 Part 2.H per instructions of SB57-88 Part 2.H Condition II, Paragraph 2, within the compliance schedule specified in Paragraph (a) of this AD.

(e) Inspect the eleven attachment holes identified in Paragraphs (c) and (d) of this AD for cracks in wing skin and rear spar lower cap aft tang using eddy current methods per SB 57-88, Part 2.H, Condition II, Paragraph 3, within the compliance schedule specified in Paragraph (a) of this AD.

(f) If cracks are found, as a result of the inspections of Paragraphs (a) or (e) of this AD, repair prior to further flight as indicated:

1. If cracks are less than 2.5 inches in length, rework in accordance with appropriate Condition of Service Sketch (SS) 3154, or Paragraph (f)(2) of this AD. Rework per SS 3154 requires repetitive inspections per Paragraphs (a) and (e) of this AD at intervals not to exceed: 1200 hours additional time in service since the last inspection for Conditions I and VI of SS 3154 or 1800 hours additional time in service for Conditions II through V of SS 3154, and repair within 3600 additional hours time in service subsequent to rework per Paragraph (f)(2) of this AD.

2. Repair cracks which are 2.5 inches in length or greater, but less than 7.0 inches in length per SB57-88, Part 2.H, Condition I, Paragraph 3.

3. Repair cracks which are 7.0 inches in length or greater after obtaining approval of the proposed repair from the Chief, Aircraft Engineering Division, FAA Western Region. Submit exact location and dimension of crack with the proposed repair.

(g) If no cracks are found as a result of inspections of Paragraphs (a) and (e) of this AD, coin six holes outboard of wing station Xcw=69.500 per SB57-88 Part 2.H, Condition II, Paragraph 4, and revert to repetitive inspection requirements of Paragraph (i) of this AD.

(h) Return the aircraft to serviceable condition per the appropriate instructions of SB57-88 prior to flight.

(i) Conduct repetitive visual inspections per Paragraph (a) and eddy-current inspection of the 11 attachment holes per Paragraph (e) at intervals not to exceed 3,600 hours time in service since the last such inspection. (Note: Do Not re-ream the eleven attachment holes inboard of station Xcw=69.500 after the initial inspection of Paragraph (e) of this AD.)

(j) Installation of the preventive modification per S/B 57-88, Part 2.H, Condition I, Paragraph 3, eliminates the requirement for repetitive inspections required by Paragraph (i) of this AD.

(k) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD.

(l) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.

This amendment becomes effective October 23, 1980.

FOOTER: