AD 80-06-04 R1

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AD Number:
80-06-04 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-9-10 through -40 and (Military) C-9 Series Aircraft
Subject:
Main Landing Gear Attach Fittings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/14/1984
Make:
The Boeing Company
Model:
DC-9-11 | DC-9-12 | DC-9-13 | DC-9-14 | DC-9-15 | DC-9-15F | DC-9-21 | DC-9-31 | DC-9-32 | DC-9-32 (...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Superseded AD: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Superseded By: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: 80-06-04 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4909

AD NUMBER:   80-06-04 R1

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-9-10 through -40 and (Military) C-9 Series Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective October 14, 1984.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-06-04 R1 MCDONNELL DOUGLAS: Amendment 39-3716 as amended by Amendment 39-4909. Applies to DC-9-10 through -40 and (Military) C-9 series aircraft, certificated in all categories, which correspond to the factory serial numbers listed in McDonnell Douglas DC-9 Service Bulletin 57-125, R4, dated June 21, 1983, (hereinafter referred to as SB 57-125, R4) except those airplanes previously modified per Option I of McDonnell Douglas DC-9 Service Bulletin 57-125, original issue, or subsequent revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

Compliance required as indicated.

To detect cracks and prevent failure of the main landing gear attach fittings, made from 7079-T6 materials identified with basic part (P/Ns) 5911258, 5919289, and 5924841, accomplish the following:

(a) Within the next 1,000 hours time in service or 125 calendar days, whichever comes first, after the effective date of this AD, for fittings on airplanes F/N 1 through 414 which have not been shotpeened and the spot faces have not been sealed, and unless already accomplished, inspect the fittings per Option 2, Phase I, Figure 1 of SB 57-125, R4.

(b) Within the next 3,200 hours time in service or 375 calendar days, whichever comes first, after the effective date of this AD, for airplanes F/N 415 through 655, and for airplanes F/N 1 through 414, which have been shotpeened per AD 72-02-03, but the spot faces have not been sealed, and for those which have existing approved treated crack or approved crack rework, inspect the fittings per Option 2, Phase I, Figure 1 of SB 57-125, R4.

(c) Within the next 6,400 hours time in service or 750 calendar days, whichever comes first, after the effective date of this AD, for airplanes F/N 656 through 742, and for airplanes F/N 1 through 655, with uncracked fittings which have been shotpeened per AD 72-02-03, and the spot face is sealed per McDonnell Douglas DC-9 Service Bulletin 57-101, inspect the fittings per Option 2, Phase I, Figure 1 of SB 57-125, R4.

NOTE (1): The Table and General Note 2 of the accomplishment instructions of SB 57-125, R4, covers the schedules of paragraphs (a), (b), (c), and (d).

NOTE (2): The initial and repetitive inspections per Option 2, Phase I, require only five (5) bolts to be removed. (Ref: Crack Locations 2, 9, 11, and 18, View "G-G," page 27, SB 57-125, R4.)

(d) Prior to September 1, 1985, inspect the area of the MLG attach fitting under the lower inboard flange ends of the lower auxiliary spar cap end fitting (reference crack location 20) in accordance with SB 57-125, R4. Perform rework as outlined in SB 57-125, R4 (Option II; Phase I, II, or III), and repetitively inspect at intervals specified in SB 57-125 R4, page 15, until terminating action is accomplished in accordance with paragraph (j), below.

(e) If cracks are found during the inspections of paragraphs (a), (b), (c), or (d) in areas identified as Crack Locations 1, 3, 4, 6, and 19, which do not extend beyond the limits given in General Note 11 of the accomplishment instructions of SB 57-125, R4, before further flight:

(1) Replace the fittings per Option 1 of SB 57-125, R4; or

(2) Treat the cracks per Phases IV through VII of the accomplishment instructions in SB 57-125, R4, and reinspect the fittings per Option 2, Phase I, Figure 1 of SB 57-125, R4, at intervals not to exceed 3,200 hours time in service or 375 calendar days, whichever occurs first.

(f) If cracks are found during the inspections of paragraphs (a), (b), (c), or (d) which meet any of conditions of General Note 12 of the accomplishment instructions of SB 57-125, R4, before further flight, replace the fittings per Option 1 of the service bulletin.

(g) If cracks are found during the inspections of paragraphs (a), (b), (c), or (d) in areas identified as Crack Locations 8, 11, 13, 14, and 15 which are less than 1-1/2 inches long and can be removed per the instructions on General Note 12.B of SB 57-125, R4, or cracks in areas identified as Crack Locations 5 and 12 which are less than 1-1/2 inches, or cracks in Location 17 which are less than 1/2 inch long, which can be removed per the instructions of General Note 12.D of SB 57-125, R4, before further flight:

(1) Replace the fitting per Option 1 of SB 57-125, R4; or

(2) Rework cracks per General Notes 12.B or 12.D, as applicable, of accomplishment instructions of SB 57-125, R4, and reinspect the fitting per Option 2, Phase I, Figure 1 of SB 57-125, R4, at intervals not to exceed 3,200 hours time in service or 375 calendar days, whichever comes first.

(h) For fittings which have been inspected per paragraphs (a), (b), (c), or (d), and which have not been modified per SB 57-125, R4, Phase II or Phase III, or by an equivalent modification:

(1) Replace the fitting per Option 1 of SB 57-125, R4; or

(2) If no cracks are found, reinspect the fitting per Option 2, Phase I, Figure 1 of SB 57-125, R4, at intervals not to exceed 3,200 hours time in service or 375 calendar days, whichever comes first; or

(3) If no reworked cracks exist and/or no new cracks are found, and the preventative shotpeen and anti-corrosion rework of AD 72-02-03 has been accomplished, and the spot faces have been sealed in production or per SB 57-101, reinspect the fitting per Option 2, Phase I, Figure 1 of SB 57-125, R4, at intervals not to exceed 6,400 hours time in service or 750 calendar days, whichever comes first; or

(4) If no reworked cracks exist and/or no new cracks are found, accomplish the preventative modification per Option 2, Phase II of SB 57-125, R4, and reinspect the fitting per Option 2, Phase I, Figure 1 of SB 57-125, R4, at intervals not to exceed 6,400 hours time in service or 750 calendar days, whichever comes first; or

(5) If no reworked cracks exist and/or no new cracks are found, accomplish the preventative modification per Option 2, Phase III of SB 57-125, R4, and reinspect the fitting per Option 2, Phase I, Figure 1 of SB 57-125, R4, at intervals not to exceed 9,600 hours time in service or 1,125 calendar days, whichever comes first.

(i) If cracks are found in locations in the fitting other than those identified in SB 57-125, R4, before further flight, replace the fitting per Option 1 of SB 57-125, R4, or rework in a manner approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

(j) Terminating Action: The repetitive requirements of this AD may be discontinued upon replacement of the existing 7079-T6 fitting with a new 7075-T73 fitting in accordance with Option I of SB 57-125, original issue, or subsequent revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

(k) Accomplishment of any portion of the inspections, treatments, rework or modifications authorized in McDonnell Douglas DC-9 Service Bulletins 57-76, 57-86, 57-88, and 57-101 required by AD 72-02-03, and which are also outlined in SB 57-125, may be considered as equivalent to that requirement of this AD.

(l) 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.

(m) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

(n) Upon request of operator, an FAA maintenance inspector, subject to prior approval of the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region may adjust the initial and repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.

All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.

This supersedes Amendment 39-1378 as amended by Amendments 39-1399, 39-1766, and 39-3126 (AD 72-02-03).

Amendment 39-3716 became effective April 24, 1980.

This Amendment 39-4909 becomes effective October 14, 1984.


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