AD 70-26-01

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AD Number:
70-26-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 747 Series Airplanes
Subject:
Passenger Evacuation System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/18/1971
Make:
The Boeing Company
Model:
747-100 Series | 747-100B Series | 747-100B SUD Series | 747-200B Series | 747-200C Series | 747-200...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Superseded AD: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Superseded By: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: 70-26-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1213

AD NUMBER:   70-26-01

SUBJECT HEADING:   BOEING Model 747 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 18, 1971.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
70-26-01 BOEING: Amdt. 39-1128 as amended by Amendment 39-1213. Applies to Model 747 Series Airplanes.

Compliance required as indicated.

To prevent malfunctions resulting in unusable passenger evacuation slides and improve the overall reliability of the passenger evacuation system, accomplish the following:

(a) Within the next 300 hours' time in service after the effective date of this AD, unless already accomplished, inspect and/or modify the passenger evacuation system in accordance with the following Service Bulletins, or later FAA approved revisions, or equivalent inspections and/or modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region:

Boeing Service Bulletin 25-2031, Revision 1, dated March 20, 1970, Parts I and II; or in the alternative, Parts II and III. If Parts I and II only have been completed, accomplish Part III when the slide is again disturbed, e.g., repaired, inflated or repacked.

Boeing Service Bulletin 25-2040, Revision 1, dated October 12, 1970.
Boeing Service Bulletin 25-2046, dated May 18, 1970.
Boeing Service Bulletin 25-2052, dated May 1, 1970, or Boeing Service Bulletin 25-2068, dated August 15, 1970.
Boeing Service Bulletin 25-2070, dated July 13, 1970.
Boeing Service Bulletin 25-2110, dated November 12, 1970.
Boeing Service Bulletin 25-2137, dated November 18, 1970.
Boeing Service Bulletin 57-2013, Revision 1, dated September 28, 1970.

(b) Within the next 2,000 hours' time in service after the effective date of this AD, unless already accomplished, modify the passenger evacuation system in accordance with the following Service Bulletins, or later FAA approved revisions, or equivalent modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region:

Consolidated Controls Corporation Service Bulletin 521002-1, dated July 9, 1970.

B. F. Goodrich Service Bulletin 25-008, dated July 20, 1970, and B. F. Goodrich Service Bulletin 25-014, dated November 18, 1970.

(c) Within the next 500 hours' time in service after the effective date of this amendment to AD 70-26-01, and thereafter at intervals not to exceed 500 hours' time in service from the last determination, until the guide arm elbow pin is modified in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region, adjust the torque of nut P/N 69B11101-1, - 2, or -3, located within the guide arm of the ten passenger cabin doors, to 125-150 inch-pounds, or equivalent procedures approved by the Chief, Aircraft Engineering Division, FAA western Region.

(d) Within the next 500 hours' time in service after the effective date of this amendment to AD 70-26-01, unless already accomplished, inspect the ten passenger cabin doors per Part I of Boeing Service Bulletin 25-2092, Revision 3, dated April 30, 1971 or later FAA approved revisions, or an equivalent inspection procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(1) If this inspection per Part I establishes either that the overall distance between the stop tabs on the floor attachment fittings is within the limits of Figure 1, View AA, or that the overlap between the forward face of the slider barlock and forward floor attachment bracket is 0.25 inch or greater, no further action is required.

(2) If neither of the two conditions described in (d)(1), above, is established by the inspection per Part I of the Service Bulletin, accomplish the modifications described in Parts II or III of the Service Bulletin or later FAA approved revisions, within 500 hours' time in service from the effective date of this amendment to AD 70-26-01, unless already accomplished, or equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(3) If the operator elects to perform Part II, and thereafter the operator modifies, alters, repairs, or replaces a girt bar, a floor fitting, or floor fitting support, repeat Part I and, if necessary, Part II, prior to further flight or within 500 hours' time in service from the effective date of this amendment to AD 70-26-01, whichever occurs later. Alternately, the operator may elect to perform Part III at this time as terminating action.

(4) If the operator elects to perform Part III rather than Part II, as described in (d)(2), above, the Part III modification must be accomplished within 500 hours' time in service from the effective date of this amendment to AD 70-26-01.

(5) If the operator elects to perform Part II, per (d)(2), above, and further, if an adequate control procedure is approved by an FAA Principal Maintenance Inspector, Part III must be accomplished within 9000 hours' time in service after the effective date of this amendment to AD 70-26-01. This control procedure must assure that Part I and, if necessary, Part II are accomplished before further flight if the girt bar, a floor fitting, or the floor fitting support is modified, altered, repair or replaced. This control procedure may be discontinued when Part III is accomplished. Part III, whenever accomplished, constitutes terminating action.

(e) Within the next 2000 hours' time in service after the effective date of this amendment to AD 70-26-01, unless already accomplished, modify the passenger evacuation system in accordance with the following service bulletins, or later FAA approved revisions, or equivalent modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region:

Boeing Service Bulletin 52-2022, dated October 1, 1970.
Boeing Service Bulletin 52-2024, Rev. 1, dated March 5,1971.
Boeing Service Bulletin 52-2043, dated December 15, 1970.

(f) Within the next 3000 hours' time in service after the effective date of this amendment to AD 70-26-01, unless already accomplished, modify the passenger evacuation system in accordance with the following service bulletins, or later FAA approved revisions, or equivalent modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region:

Boeing Service Bulletin 25-2133, dated January 26, 1971.
B. F. Goodrich Service Bulletin 25-018, dated January 22, 1971.

(g) Within the next 5000 hours' time in service after the effective date of this amendment to AD 70-26-01, unless already accomplished, modify the passenger evacuation system in accordance with the following service bulletin, or later FAA approved revisions, or equivalent modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region:

B. F. Goodrich Service Bulletin 25-016, dated December 1, 1970.
Amendment 39-1128 became effective December 18, 1970.
This Amendment 39-1213 becomes effective May 18, 1971.

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