AD 82-06-02 R1

AD Final Rules - DRS_82-06-02_R.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
82-06-02 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-9-10 through -50 Series and C-9 Series Airplanes
Subject:
Horizontal Stabilizer Section Fittings And Plates
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/16/1982
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Superseded AD: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Superseded By: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: 82-06-02 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4358

AD NUMBER:   82-06-02 R1

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-9-10 through -50 Series and C-9 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 16, 1982.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
82-06-02 R1 MCDONNELL DOUGLAS: Amendment 39-4339 as amended by Amendment 39-4358. Applies to all McDonnell Douglas Model DC-9-10 through -50 Series and C-9 Series airplanes prior to fuselage number 1013 certificated in all categories.

Compliance required as indicated in the body of this AD, unless previously accomplished. To prevent failure of the horizontal stabilizer center section fittings and plates, perform the following:

A. Prior to the accumulation of 4100 flight hours total time in-service or within 1600 flight hours time in-service following the effective date of this AD, whichever comes later, but in any case not later than December 1, 1982, accomplish the following:

(NOTE: Operators who have accomplished the actions required by paragraphs (A)(1) - (A)(3) below, prior to the effective date of this AD, need not reinspect until 6400 flight hours or three (3) calendar years, whichever occurs first, following the last inspection, as required by paragraph "B" below.)

1. Visually inspect for corrosion in areas shown in McDonnell Douglas Structural Repair Manual (SRM), Chapter 55-02, Figure 12, Fitting P/N's 5912481-1, -501, -503, -505, -507.

(a) If corrosion is evident, remove corrosion per SRM Chapter 51-10-3. Reinspect to insure limits established per SRM Chapter 55-02, Figure 12, are maintained and apply corrosion inhibiting compound per SRM Chapter 51-10-3.

(b) If limits are exceeded, replace each affected part as necessary.

(c) If corrosion is not evident, apply corrosion inhibiting compound per SRM Chapter 51-10-3.

2. Visually inspect P/N 5918098-1 and -501 fitting assemblies for cracks, as outlined in SRM Chapter 55-02, Figure 13.

(a) If cracks are found, repair per SRM Chapter 55-02, Figure 13.

(b) If cracks are not found or if cracks have been repaired per (2)(a) above, apply corrosion inhibiting compound to the fitting(s) per SRM Chapter 51-10-3.

(c) If corrosion is not evident, apply corrosion inhibiting compound per SRM Chapter 51-10-3.

3. Visually inspect P/N's 9911861-1, 9911862-1, 9918440-1, and 9918441-1 plates for corrosion in areas shown in SRM Chapter 55-02, Figure 12.

(a) If corrosion is evident, remove corrosion per SRM Chapter 51-10-3. Reinspect to insure limits established per SRM Chapter 55-02, Figure 12, are maintained and apply corrosion inhibiting compound per SRM Chapter 51-10-3.

(b) If limits are exceeded, replace each affected part as necessary.

(NOTE: The removal of the upper aft plate P/N 9911862-1 and cover P/N 5910405-3 provides access to the areas required to be inspected in paragraph A.)

B. The inspections and repairs set forth in paragraph A above must be repeated at intervals of 6400 flight hours or three (3) calendar years, whichever occurs first, until the affected parts are replaced by new parts per McDonnell Douglas DC-9 Service Bulletin 55-32, Revision 1, dated September 28, 1981, or later revisions approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region.

C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the inspection requirements of this AD.

D. Alternative means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1).

All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60).

These documents also may be examined at the FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108, or the Los Angeles Area Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California 90808.

Amendment 39-4339 became effective March 17, 1982.

This Amendment 39-4358 becomes effective April 16, 1982.


FOOTER: