AD 85-01-03

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AD Number:
85-01-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; McDONNELL DOUGLAS DC-9 and C-9 (Military) Series Airplanes
Subject:
Spoiler Drive Link And Fittings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/14/1985
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Superseded AD: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Superseded By: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: 85-01-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4977

AD NUMBER:   85-01-03

SUBJECT HEADING:   Airworthiness Directives; McDONNELL DOUGLAS DC-9 and C-9 (Military) Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 14, 1985.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
85-01-03 McDONNELL DOUGLAS: Amendment 39-4977. Applies to McDonnell Douglas Model DC-9 and C-9 (Military) series airplanes, manufacturer's fuselage numbers 1 through 1125, certificated in all categories. Compliance required as indicated, unless previously accomplished.

To prevent failures of the spoiler drive link(s), P/N 3923250-1, -501 and/or -503; and spoiler fitting(s), P/N 3923251-1 and/or -501, accomplish the following: Part I

A. Applies to McDonnell Douglas DC-9-10 through -50, and C-9 (Military) series airplanes.

1. For operators who have accomplished terminating action in accordance with Airworthiness Directive (AD) 74-16-02, Amendment 39-2213, dated May 27, 1975, within the next 3,000 flight hours or 3,000 cycles, whichever occurs first, from the effective date of this AD, and thereafter at intervals not to exceed 3,000 flight hours or 3,000 cycles, whichever occurs first, perform non-destructive inspection (NDI) in accordance with the instructions contained in McDonnell Douglas Non-Destructive Testing (NDT) Manual, TR 7-1 through 7-4, referenced in McDonnell Douglas DC-9 Service Bulletins 27-228 and/or 27-229, both service bulletins dated August 19, 1982, or later NDT Manual or Service Bulletin revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

NOTE: McDonnell Douglas Service Bulletins 27-228 and 27-229, both dated August 19, 1982, and 27-240, dated June 30, 1983, are hereinafter referred to as SB 27-228, SB 27-229, and SB 27-240.

2. For operators who have instituted the program of visual/repetitive inspections in accordance with AD 74-16-02, Amendment 39-2213, dated May 27, 1975, at the next scheduled repetitive inspection, comply with the instructions in accordance with this AD, as applicable.

3. For operators who have not implemented AD 74-16-02, Amendment 39-2213, dated May 27, 1975:

a. Within the next 300 flight hours or 300 cycles, whichever occurs first, and thereafter at intervals not to exceed 300 flight hours or 300 cycles from the effective date of this AD:

(1) Visually inspect the exposed surfaces on the forward and aft lugs, including the areas surrounding the grease fittings on the spoiler actuating link, and

(2) Visually inspect the exposed surface and areas surrounding the grease fitting on the spoiler fitting.

b. At or prior to the accumulation of an additional 1,000 flight hours or 1,000 cycles, whichever comes first, from first visual inspection on these parts, and thereafter at intervals not to exceed 3,000 flight hours or 3,000 cycles, whichever comes first, institute the program of NDI inspections as required by Part I, paragraph A.1, above, until terminating action in accordance with Part I, Paragraph A.6., below, is accomplished.

NOTE: The requirements for visual inspections may be terminated upon instituting the NDI program specified in Part I, paragraph A.1, of this AD.

4. If no cracks are found in the spoiler drive link or fitting assemblies in the areas identified by Figures 1 through 7 of NDT Manual TR 7-1 through TR 7-4 referenced in SB 27-228 and/or SB 27-229, or a FAA approved alternate NDT method in accordance with Part I, paragraph C.3., below, continue repetitive inspections in accordance with Part I, paragraph A.1., above, until such time terminating action is accomplished in accordance with Part I, paragraph A.6., below.

5. If cracks are found in the spoiler drive links, or fittings in areas identified by Part I, paragraph A.3., above.

a. Replace with new flight spoiler components, in accordance with paragraph 2. of the Accomplishment Instructions, Figure 1, of SB 27-240.

b. Replace with spoiler drive link, or aft attach fitting, and continue repetitive inspection in accordance with Part I, paragraph A.1., above, until terminating action is accomplished in accordance with Part I, paragraph A.6., below.

6. Replacement of the flight spoiler components with new components in accordance with SB 27-240, dated June 30, 1983, or later FAA approved revisions, constitutes terminating action for repetitive inspection requirements of this AD.

NOTE: Accomplishment of the preventive modification in accordance with SB 27-240 will constitute terminating action for the repetitive inspection requirements of this AD.

B. Applies to McDonnell Douglas DC-9-80 series airplanes:

1. Airplanes that are not affected by AD 74-16-02, Amendment 39-2213, dated May 27, 1975, but are affected by McDonnell Douglas Report MDC-J8855, Revisions A through G, or later FAA approved revisions, will continue existing inspection program. This program performs NDT inspections of the flight spoiler drive links or fittings, as follows:

a. One time visual inspection prior to exceeding 5000 total airplane flight hours.

b. Initial ultrasonic and/or eddy current inspection within 1000 flight hours after visual inspection.

c. Repetitive ultrasonic and/or eddy current inspections at intervals not to exceed 3000 flight hours or 3000 landings whichever occurs first, until Service Bulletin 27-240 is accomplished.

d. Replacement of flight spoiler drive link with a new P/N 3923250-503 link requires reinstituting the repetitive ultrasonic and/or eddy current inspections within 6000 flight hours or 6000 landings, whichever occurs first.

e. Replacement of flight spoiler drive fitting with new P/N 3923251-1 "G" or -501 fitting assembly requires reinstituting the repetitive ultrasonic and/or eddy current inspections within 6000 flight hours or 6000 landings, whichever comes first.

2. Accomplishment of the preventative modifications in accordance with SB 27-240 will constitute terminating action for the special inspection requirements listed in McDonnell Douglas Report MDC-J8855, Parts III and IV, Revisions A through G, or later FAA approved revisions.

C. Applies to all McDonnell Douglas DC-9 and Military C-9 series airplanes:

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

2. Upon the request of an operator, an FAA Maintenance Inspector, subject to approval by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of that operator, if the request contains substantiating data to justify the change for that operator.

3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

NOTE: For purposes of this AD, if the time-in-service hours of either the spoiler actuating link or the spoiler fitting cannot be established, the part will be considered to have the same number of time-in-service hours as the airplane on which it is installed.

Part II

Applies to all DC-9 series aircraft, fuselage numbers 1 through 1125, certificated in all categories, as indicated below:

To provide crews with operation information should spoiler float occur, evidenced by abrupt roll, and to provide for a permanent change in the "Emergency Procedures" Section of the FAA approved Airplane Flight Manual (AFM) (and appropriate AFM sections of the operator's manual required by FAR 121.133 and 121.141), accomplish the following:

A. PLACARD

Within 30 days after effective date of this AD, unless already accomplished, install a placard as close as practicable to the flap position indicator, containing the following wording or an equivalent wording as approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, reading as follows:

DC-9-10

"Flap selection excess 20 degrees must be made prior to 1000 feet AGL. See Section I, AFM for alternate procedures." (The last sentence may be omitted from the placard if the use of alternate landing flap setting is not desired.)

DC-9-20, -30, -40, -50, and C-9 (Military Series)

"Flap selection excess 25 degrees must be made prior to 1000 feet AGL. See Section I, AFM for alternate procedures." (The last sentence may be omitted from the placard if the use of alternate landing flap setting is not desired.)

DC-980 Series

"Flap selection excess 28 degrees must be made prior to 1000 feet AGL. See Section I, AFM for alternate procedures." (The last sentence may be omitted from placard if the use of alternate landing flap setting is not desired.)

B. LIMITATIONS

1. The limitations set forth below are effective as of June 14, 1974, for the Models DC-9-10 through -40 series and C-9A and C-9B airplanes; and effective within 30 days after the effective date for the Models DC-9-50 and -80 series airplanes.

2. Within 30 days after the effective date of this AD, unless already accomplished, incorporate the "Limitations" set forth below into the Airplane Flight Manual (AFM). Operators must initiate actions to notify and ensure that the flight crewmembers are apprised of these limitations.

DC-9-10 Series

Sec. I Limitations: (New Title) "Flaps":

"Flap selection in excess of 20 degrees must be made prior to descending below 1000 feet above ground level except for the following:

Approach and landing may be made with a maximum of 30 degree flap when 15 percent is added to the 50 degree flap landing field length."

Sec. I Limitations: Performance and Operating Limitations. Add a new paragraph as follows:

"When using the 30 degrees flaps for landing, the maximum permissible quick turn around landing weight shown on the plot 'Maximum Permissible Quick Turn Around Landing Weight Flaps Down' in Section IV must be reduced by 15 percent."

DC-9-20, -30, -40, -50, and C-9 (Military Series)

Sec. I Limitations: (New Title) "Flaps"

"Flap selection in excess of 25 degrees must be made prior to descending below 1000 feet above ground level except for the following:

Approach and landing may be made with a maximum of 25 degree flap when 20 percent is added to the 50 degree flap landing field length."

Sec. I Limitations: Performance and Operating Limitations. Add new paragraph as follows:

"When using the 25 degree flap for landing, the maximum permissible quick turn around landing weight shown on the plot 'Maximum Permissible Quick Turn Around Landing Weight Flaps Full Down' in Section IV must be reduced by 20 percent."

DC-9-80 Series

Sec. I Limitations: "Flaps"

"Flap selection in excess of 28 degrees must be made prior to descending below 1000 feet above ground level."

3. The above "Limitations" may be terminated, and the "Placard" removed when operator(s) have implemented the repetitive inspections required by Part I of this AD.

C. EMERGENCY PROCEDURES

1. The Emergency Procedures set forth below are effective as of June 14, 1974, for the Models DC-9-10 through -40 series and C-9A and C-9B airplanes; and effective within 30 days after the effective date of this AD for the Models DC-9-50 and -80 series airplanes.

2. Within 30 days after the effective date of this AD, unless already accomplished, incorporate the "Emergency Procedures" set forth below into the Airplane Flight Manual. These procedures constitute a permanent change to the manual. Operators must initiate action to notify and ensure that flight crewmembers are apprised of this change.

DC-9-10, -20, -30, -33F, -40, and C-9 (Military Series)

Section II: Emergency Procedure (New Title) "Spoiler Float";

"Should rapid roll develop during extension of flap to 50 degrees, retract immediately to single engine landing flap setting. Adjust speed as required."

DC-9-34, -50 Series

Section II: Emergency Procedure (New Title) "Spoiler Float";

"Should rapid roll develop during extension of flap beyond 25 degrees, retract immediately to single engine landing flap setting. Adjust speed as required."

DC-9-80 Series

Section II: Emergency Procedure (New Title) "Spoiler Float";

"Should rapid roll develop during extension of flap beyond 28 degrees, retract immediately to single engine landing flap setting. Adjust speed as required."

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 also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.

This supersedes AD 74-16-02, Amendment 39-2213, dated May 27, 1975.

This amendment becomes effective February 14, 1985.


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