AD 74-10-13

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AD Number:
74-10-13
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 707 and 720 Airplanes
Subject:
Auxiliary Hydraulic System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/14/1974
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Superseded AD: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Superseded By: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: 74-10-13
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1845

AD NUMBER:   74-10-13

SUBJECT HEADING:   BOEING Model 707 and 720 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 14, 1974.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
74-10-13 BOEING: Amendment 39-1845. Applies to all Model 707 and 720 airplanes having 6,000 hrs., or more, time in service, certificated in all categories.
Compliance is required as indicated, unless already accomplished.
To prevent excessive non-recoverable internal hydraulic leakage in the auxiliary hydraulic system and the possible loss of aircraft direction control at critical air speeds, accomplish the following:
PART I
(a) PART I of this AD applies to airplanes which will be used for flight crew training.
(b) Prior to further flight for crew training, and thereafter at intervals not to exceed 2,000 hours time in service from the last inspection, the airplane auxiliary hydraulic system must be inspected and replaced or reworked, as necessary, in accordance with the following:
(1) Inspect for evidence of internal leakage per the information contained in Boeing Alert Service Bulletin 3154 dated April 12, 1974, or later FAA approved revisions of Boeing Alert Service Bulletin 3154 or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.
(2) Airplanes with an auxiliary hydraulic system having internal leakage equal to or greater than 1.0 GPM but less than 3.0 GPM may not be used in training or revenue service but may only be flown in accordance with FAR 21.197 to a maintenance base for replacement or rework, as necessary, of the defective auxiliary hydraulic system components.
(3) Airplanes with an auxiliary hydraulic system having 3.0 GPM, or more, internal leakage must have the defective auxiliary hydraulic system components replaced or overhauled, as necessary, prior to further flight.
PART II
(a) PART II of this AD applies to airplanes which have not been inspected and reworked, as necessary, in accordance with Amendment 39-1753 (F. R. Doc. 73-25927), AD-73-25-2.
(b) Within 300 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 2,000 hours time in service from the last inspection, accomplish the following:
(1) Inspect for evidence of internal leakage and replace or rework, as necessary, per the information contained in Boeing Alert Service Bulletin 3154 dated April 12, 1974, or later FAA approved revisions of Boeing Alert Service Bulletin 3154 or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.
(2) Airplanes with an auxiliary hydraulic system having internal leakage equal to or greater than 1.0 GPM but less than 3.0 GPM may not be used in revenue service but may only be flown in accordance with FAR 21.197 to a maintenance base for replacement or rework, as necessary, of the defective auxiliary hydraulic components.
(3) Airplanes with an auxiliary hydraulic system having 3.0 GPM, or more, internal leakage must have the defective auxiliary hydraulic system components replaced or overhauled, as necessary, prior to further flight.
PART III
(a) PART III of this AD applies to airplanes which have been inspected and reworked, as necessary, in accordance with Amendment 39-1753 (F. R. Doc. 73-25927), AD-73-25-2.
(b) Within 600 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 2,000 hours time in service from the last inspection, accomplish the following:
(1) Inspect for evidence of internal leakage and replace or rework, as necessary, per the information contained in Boeing Alert Service Bulletin 3154 dated April 12, 1974, or later FAA approved revisions of Boeing Alert Service Bulletin 3154, or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.
(2) Airplanes with an auxiliary hydraulic system having internal leakage equal to or greater than 1.0 GPM but less than 3.0 GPM, may not be used in revenue service but may only be flown in accordance with FAR 21.197 to a maintenance base for replacement or rework, as necessary, of the defective auxiliary hydraulic system components.
(3) Airplanes with an auxiliary hydraulic system having 3.0 GPM, or more, internal leakage must have the defective auxiliary hydraulic system components replaced or overhauled, as necessary, prior to further flight.
For the purpose of complying with the repetitive periodic inspection requirement of this AD, the 2,000 hours time in service may be adjusted by submitting substantiating technical data through the FAA assigned maintenance inspector for the approval of the Chief, Engineering and Manufacturing Branch, Flight Standards Division, FAA, Northwest Region.

This AD Amendment 39-1845 supersedes AD 73-25-2.
This Amendment becomes effective May 14, 1974.

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