AD 71-03-02

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AD Number:
71-03-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 707 and 720 Series Airplanes
Subject:
Elevator Aft Quadrant
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/13/1971
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Superseded AD: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Superseded By: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: 71-03-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1151

AD NUMBER:   71-03-02

SUBJECT HEADING:   BOEING Model 707 and 720 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 13, 1971.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
71-03-02 BOEING: Amdt. 39-1151. Applies to Model 707 and 720 series airplanes listed in Boeing Service Bulletin 3003, Revision 2, dated January 15, 1971, or later FAA approved revisions.
Compliance required as indicated after the effective date of this AD.
To assure elevator aft quadrant integrity, accomplish the following inspections and rework or the equivalent inspections and rework approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(a) Within the next 15 hours' time in service unless already accomplished per Telegraphic Alert Service Bulletin 3003 dated October 16, 1970, or AD 70-22-08, perform a close visual inspection of the elevator aft control quadrant hub aft flange face and central web area for corrosion and cracks per Part I of Boeing Service Bulletin 3003, Revision 2, dated January 15, 1971, or later FAA approved revisions. If cracks are found, replace quadrant per paragraph (d).
(b) Within the next 750 hours' time in service unless already accomplished, inspect the aft flange face and central web of the elevator aft quadrant for corrosion and cracks per Parts I and II of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions. Accomplish a micrometer check of the quadrant torque tube diameter for ovalness in both the "x" and "y" axes as shown in Fig. 1 of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions.
(1) If the torque tube is either round or oval within limits per Part II of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions, perform periodic close visual inspections at intervals not to exceed 750 hours' time in service. On or before 1500 hours' time in service, initiate the dye penetrant or eddy current and torque check inspection program per Part III of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions. The quadrant assembly may be retained in service under dye penetrant or eddy current inspection surveillance at intervals not to exceed 1500 hours' time in service until it is either replaced or overhauled per (c).
(2) If the torque tube exceeds the limits of ovalness specified in Part II of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions, conduct a dye penetrant or eddy current inspection and torque check per Part IV of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions prior to further flight.
(3) If, after performing the inspection and torque check per (2) above, the torque tube diameter difference is less than .004, the quadrant assembly may be retained in service under dye penetrant or eddy current inspection surveillance at intervals not to exceed 1500 hours' time in service until it is either replaced per (d) or overhauled per (c).
(4) If, after completing the inspection and torque check per (2) above, the torque tube dimensional difference is still greater than .004, replace the quadrant assembly per (d).
(c) On or before 12,000 hours' time in service unless already accomplished, overhaul or replace the quadrant assembly per Part V of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions.
(d) If, as a result of any of the foregoing inspections, the quadrant assembly shows signs of cracks, or the torque tube ovalness is beyond limits after the torque check, replace the quadrant assembly prior to further flight with either an "Existing" quadrant assembly reworked in accordance with Part V of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions, or by an "Equivalent" new quadrant assembly as identified in table II of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions.
(e) The inspections required by this AD may be discontinued upon replacement of the aft quadrant assembly by an "Existing" quadrant assembly reworked in accordance with Part V of the Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions, or by an "Equivalent" new quadrant assembly as identified in table II of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions.
This amendment supersedes Amendment 39-1101, 35 F.R. 16791, AD 70-22-08.
This amendment becomes effective February 13, 1971.

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