AD 63-16-01

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AD Number:
63-16-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Models 707 and 720 Series Aircraft
Subject:
Thrust Reverser Sleeve
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/04/1964
Make:
The Boeing Company
Model:
707-100 Long Body | 707-100B Long Body | 707-100B Short Body | 707-200 | 707-300 Series | 707-300B S...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Superseded AD: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Superseded By: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: 63-16-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   63-16-01

SUBJECT HEADING:   BOEING Models 707 and 720 Series Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective March 4, 1964.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   63-16-01 BOEING: Amdt. 596 Part 507 Federal Register August 3, 1963. Applies to All Models 707 and 720 Series Aircraft Equipped with Pratt & Whitney JT3D-1 or -3 engines.

Compliance required as indicated.

To prevent inadvertent aft thrust reverser sleeve actuation, compliance with the following is required:

(a) Within 300 hours' time in service after the effective date of this airworthiness directive, unless already accomplished within the last 200 hours' time in service, and within each 500 hours' time in service thereafter until compliance with (d), inspect the upper latch lock hook for evidence of interference with the latch roller support structure. This inspection shall be done as follows or in accordance with an FAA-approved equivalent procedure:

(1) Remove the access panel in the aft reverser sleeve to gain access to the upper latch lock (P/N 65-10567).

(2) Disengage the upper and lower latch locks and move the sleeve 5 inches aft from the fully closed position.

(3) Force the aft end of the upper latch lock horizontally to the limit of its travel and hold it in that position.

(4) Move the sleeve forward and determine by using a feeler gauge, if the hook end of the latch clears the roller support structure by 0.05 inch minimum while the hook is in position (3).

(5) Repeat (3) and (4) with the hook displaced to its limit in the opposite direction.

(6) If the hook end of the latch clears the roller support structure on either side by less than 0.05 inch the latch installation must be reworked in accordance with (b) before further flight.

(b) Rework the latch installation by replacing the latch pivot bearing with a new bearing, BAC-B10A-649 or BAC-B10A-649A, roller swaged in place per BAC Process Specification 5435 or secured by an FAA approved equivalent means, or by replacing the latch assembly, P/N 65-10567, with a new or reworked assembly. When replacing the latch bearing or latch assembly install an AN 960C616L washer on each side of the latch pivot bearing to provide additional support. After rework, the latch hook must clear the roller support structure by 0.05 inch minimum.

(c) Unless already accomplished, within 500 hours' time in service after the effective date of this AD, provide an indexing stripe in accordance with Boeing Service Bulletin No. 1799, or equivalent, to the inboard surface of the strut and sleeve to give visual indication of the aft reverser sleeve position both on the ground and inflight. To insure alignment of the stripe following replacement, removal, or rework of either the aft sleeve or strut, remove the old stripe and apply a new one in accordance with Boeing Service Bulletin No. 1799, or equivalent. Approval of any equivalent means shall be processed through Engineering and Manufacturing Branch, FAA Western Region, Los Angeles, California.

(d) Within 2,400 hours' time in service after the effective date of this AD, unless already accomplished, accomplish the following:

(1) Install a new latch pivot bearing (BAC-B10A-649A) in the upper latch assembly in accordance with Boeing Service Bulletin No. 1787, or replace the latch assembly with a new or reworked assembly (P/N 65-10567-A) which incorporates the new bearing (BAC- B10A-649A).

(2) Provide a means of preventing the upper latch hook from jamming into the latch roller support structure in accordance with Boeing Service Bulletin No. 1809 or equivalent. Approval of any equivalent means shall be processed through Engineering and Manufacturing Branch, Western Region, Los Angeles, California.

(e) At each engine replacement after incorporation of (d)(1) and (2), determine if the upper latch lock pivot bearing is in serviceable condition and if it is properly retained in its housing. If necessary, rework the upper latch assembly as required to return it to a serviceable condition in accordance with Boeing Service Bulletin No. 1787.

(f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the 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 such operator.

(g) The aft thrust reverser position indicating switch may be relocated in accordance approved equivalent. Approval of any equivalent means shall be processed through the Engineering and Manufacturing Branch, Western Region, Los Angeles, California. When the approved switch relocation is incorporated, compliance with the provisions of paragraphs (a) through (e) of this AD is no longer required. (Boeing Service Bulletin No. 1896 pertains to this subject.)

(Boeing Service Bulletin Nos. 1787, 1799 and 1809 pertain to this subject.)

This directive effective September 6, 1963.

Revised March 4, 1964.


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