AD 71-09-02

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AD Number:
71-09-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 707/720 Series Airplanes
Subject:
Rudder Hydraulic Support Fitting
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/02/1971
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Superseded AD: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Superseded By: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: 71-09-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1276

AD NUMBER:   71-09-02

SUBJECT HEADING:   BOEING Model 707/720 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 2, 1971.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   71-09-02 BOEING: Amendment 39-1197 as amended by Amendment 39-1225 and 39-1254 is further amended by Amendment 39-1276. Applies to Model 707/720 series airplanes equipped with 7079/T6 rudder hydraulic power actuator support fittings.
Compliance required as indicated.
To detect cracks which might result in failure of the rudder hydraulic power actuator support fitting and to prevent additional cracking of the fitting in the vicinity of the actuator attachment holes, accomplish the following:
(a) For airplanes previously reworked in accordance with paragraph (b) of AD 69-13-02, as amended by Amendment 39-1174 effective March 18, 1971, within the next 100 hours' time in service after the effective date of this AD unless already accomplished in accordance with paragraph (d)(1) of that AD, perform either an ultrasonic inspection, or, after removal of bushings, an eddy current inspection to detect evidence of cracks in the support fitting.
(b) Unless already accomplished within the last 300 hours' time in service prior to the effective date of this AD, within the next 100 hours' time in service after the effective date of this AD, perform either another ultrasonic inspection or, with bushings removed, an eddy current inspection of all fittings previously inspected by ultrasonic means.
(c) At intervals not to exceed 400 hours' time in service after the last ultrasonic inspection, reinspect by ultrasonic means all fittings previously inspected in that manner in compliance with (a) and (b), above, until an eddy current inspection, with bushings removed, is performed per (d), below.
(d) Within 1200 hours' time in service after the effective date of this AD but no later than 1200 hours' time in service after the last eddy current inspection with bushings removed, remove all bushings and perform an eddy current inspection of the fitting.
(e) After accomplishment of the eddy current inspection per (b) or (d), above, and until affected fittings are replaced or modified per (f) or (i), below, inspect such fittings by ultrasonic and/or eddy current as follows:
(1) Inspect by ultrasonic means at intervals not to exceed 650 hours' time in service until the next such inspection after the effective date of this amendment. Thereafter, inspect either by ultrasonic means at intervals not to exceed 325 hours' time in service or by eddy current, with bushings removed, at intervals not to exceed 650 hours' time in service.
(2) Inspect by eddy current, with bushings removed, at intervals not to exceed 1200 hours' time in service until the next such inspection after the effective date of this amendment. Thereafter, inspect either by ultrasonic means at intervals not to exceed 325 hours' time in service or by eddy current, with bushings removed, at intervals not to exceed 650 hours' time in service.
(3) After the next 100 hours' time in service following the effective date of this amendment, perform all ultrasonic and eddy current inspections with the equipment and procedures outlined in Boeing Service Bulletin No. 2903, Revision 6, dated June 4, 1971, or later FAA approved revision, or in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region.
(f) When any fitting inspected in accordance with the foregoing paragraphs or paragraph (g), below, exhibits evidence of a crack which cannot be reworked within the hole oversize limits outlined in Boeing Service Bulletin 2903, Revision 6, dated June 4, 1971, or later FAA approved revision, either: replace the fitting prior to further flight with a new fitting made of 7075-T73 material; modify the fitting and install a steel replacement lug assembly in accordance with FAA- approved Boeing Service Bulletin 3042; or accomplish another replacement or modification approved by the Chief, Aircraft Engineering Division, FAA Western Region.
(g) When any fitting inspected in accordance with paragraphs (a) through (e), above, or in accordance with this paragraph, exhibits evidence of a crack which can be reworked within the hole oversize limits outlined in Boeing Service Bulletin 2903, Revision 6, dated June 4, 1971, or later FAA-approved revision, the fitting may be returned to service, provided:
(1) The fitting is reworked and new bushings are fabricated in accordance with Part II of Boeing Service Bulletin 2903, dated June 2, 1969, or later FAA approved revision;
(2) The new bushings are installed in the fitting in accordance with (h), below; and
(3) The fitting is inspected thereafter by ultrasonic means or, with bushings removed, by eddy current at intervals not to exceed 325 hours' time in service. After the next 100 hours' time in service following the effective date of this amendment, perform all such inspections in accordance with (e)(3), above. The intervals within which the eddy current inspections must be performed may then be increased to 650 hours' time in service.
(h) Fittings inspected or reinspected by eddy current technique to comply with paragraphs (a) through (e) and (g), above, and fittings eligible for rework in accordance with (g), above, may be returned to service when the bushings are installed or reinstalled in the manner outlined in Boeing Service Bulletin 2903, Revision 5, dated February 3, 1971, or later FAA- approved revision.
(i) Before further flight after January 1, 1972, either:
(1) Replace all 7079-T6 fittings with fittings made of 7075-T73 material; or
(2) Modify the 7079-T6 fitting and install a steel replacement lug assembly in accordance with FAA-approved Boeing Service Bulletin 3042; or
(3) Accomplish another replacement or modification approved by the Chief, Aircraft Engineering Division, FAA Western Region.
The special inspections prescribed by this AD on any airplane are terminated when the fitting is replaced or modified in accordance with this paragraph.
(j) When a fitting is found to exhibit evidence of a crack, the airplane may not be ferried.
(k) After the effective date of this AD, actuator support fittings not previously reworked by the installation of aluminum-nickel-bronze bushings in accordance with paragraph (b) of AD- 69-13-02, effective June 6, 1969, must be inspected, reworked, or replaced as follows:
(1) Before further flight remove all bushings and perform an eddy current inspection of the support fitting.
(2) Before further flight, replace any fitting found to be cracked beyond rework limits, in accordance with (f), above.
(3) Any fitting found cracked within rework limits may be returned to service if reworked in accordance with (g), above, and the new bushings are installed in accordance with (h), above.
(4) Before further flight, fittings inspected in accordance with (k)(1), above, and found to be uncracked must be modified to incorporate flanged aluminum-nickel-bronze bushings described by Paragraph C of Boeing Service Bulletin 2903, dated June 2, 1969, and by Part II - Bushing Replacement of that Service Bulletin, or in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region, unless the fitting is replaced or modified in accordance with (f) above. Installation of flanged bushings must be performed in accordance with (h), above.
(5) All fittings modified per (k)(4) to incorporate flanged aluminum-nickel-bronze bushing must be reinspected in the manner and within the corresponding intervals specified in (e), above, until replaced in accordance with (k)(6).
(6) All 7079-T6 fittings must be replaced before further flight after January 1, 1972, in accordance with (i), above.
(l) Following each actual or simulated #3 or #4 engine power failure, or flight with #3 or #4 engine shutdown, or prior to ferry flight with #3 or #4 engine inoperative, perform either an ultrasonic inspection or, with bushings removed, an eddy current inspection before further flight to detect any evidence of a crack in the rudder actuator support fitting. Any fitting exhibiting evidence of a crack must be replaced per (f) above, or reworked per (g) above, before further flight.
AD 71-09-02 Amendment 39-1197 supersedes amendment 39-786 (34 F.R. 9748), AD 69- 13-02, as amended by Amendment 39-800, (34 F.R. 12214), and Amendment 39-1174, (36 F.R. 5209).
Amendment 39-1197 became effective April 27, 1971.
Amendment 39-1225 became effective June 8, 1971 for all persons except those to whom it was made effective immediately by telegram dated May 14, 1971.
Amendment 39-1254 became effective August 3, 1971.
This Amendment 39-1276 becomes effective September 2, 1971.

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