AD 91-22-04

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AD Number:
91-22-04
Document Type:
AD Final Rules
Docket Number:
91-NM-105-AD
Subject Heading:
Airworthiness Directives; BOEING Model 707/720 Series Airplanes
Subject:
Main Cargo Door
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/29/1991
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 91-22-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   91-NM-105-AD

AMENDMENT:   39-8064

AD NUMBER:   91-22-04

SUBJECT HEADING:   Airworthiness Directives; BOEING Model 707/720 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 29, 1991.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
91-22-04 BOEING: Amendment 39-8064. Docket No. 91-NM-105-AD.

Applicability: Model 707/720 series airplanes with a main cargo door, listed in Boeing Service Bulletin 3477, dated July 26, 1990; and Models 727-100C and 727-200F series airplanes, listed in Boeing Service Bulletin 727-52-0142, dated July 26, 1990; certificated in any category.

Compliance: Required as indicated, unless previously accomplished, or unless the main cargo door has been deactivated in accordance with Boeing Service Bulletin 3311, dated May 26, 1978 (for Model 707/720 series airplanes), or Boeing Service Bulletin 727-29-0053, dated July 8, 1977 (for Model 727 series airplanes).

To prevent inadvertent opening of the main cargo door, accomplish the following:

(a) Within the next 30 days after the effective date of this AD, change the operating procedures for the main cargo door to include the following requirements, and thereafter comply with those revised procedures until the inspection required by paragraph (b) of this AD has been accomplished: Prior to takeoff following each operation of the door, conduct a visual verification, through the external viewports, to ensure proper engagement of the latching cams to ensure that the door is fully latched closed. This information must be relayed to and acknowledged by the flight crew.

(1) The procedures required by this paragraph must be accomplished by a qualified and trained mechanic or flight officer, and the training program must be approved by the FAA Principal Maintenance Inspector (PMI).

(2) Documentation of compliance with these procedures is required and the method of documentation must be approved by the FAA PMI.

(b) Within the next 18 months after the effective date of this AD, perform a visual inspection for wear of the mating surfaces of the pressure relief door hinge fittings and latch cams of the main cargo door, in accordance with Section III, Part I, of the Boeing Service Bulletin 3477, dated July 26, 1990 (for Model 707/720 series airplanes), or Boeing Service Bulletin 727-52-0142, dated July 26, 1990 (for Model 727 series airplanes).

(1) If wear exceeds the limits specified in the applicable service bulletin: Prior to further flight, replace worn parts, as follows. Do not intermix original configuration parts with modified parts in the same door.

(i) Replace worn parts with modified parts in accordance with Section III, Part II, of the applicable service bulletin; or

(ii) Replace worn parts with airworthy parts of the original configuration in accordance with FAA-approved procedures.

(2) The inspection and replacement of parts, if necessary, in accordance with this paragraph constitutes terminating action for the special operating procedures required by paragraph (a) of this AD.

(c) Within 36 months after the effective date of this AD, accomplish the following in accordance with Section III, Part II, of Boeing Service Bulletin 3477, dated July 26, 1990 (for Model 707/720 series airplanes), or Boeing Service Bulletin 727-52-0142, dated July 26, 1990 (for Model 727 series airplanes).

(1) Replace the latch cams,

(2) Replace the latch cam bellcranks,

(3) Replace the pressure relief door hinge fittings, and

(4) Perform the operation, control, and door warning system tests.

(d) For airplanes on which the main cargo door has been deactivated:

(1) Prior to reactivating the main cargo door, accomplish the inspection required by paragraph (b) of this AD.

(2) Within the next 18 months after reactivation, or within 36 months after the effective date of this AD, whichever is later, accomplish the requirements of paragraph (c) of this AD.

(e) The accomplishment of Section III, Part II, of Boeing Service Bulletin 3477, dated July 26, 1990 (for Model 707/720 series airplanes), or Boeing Service Bulletin 727-52-0142, dated July 26, 1990 (for Model 727 series airplanes), as applicable, constitutes terminating action for the requirements of this AD.

(f) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.

(g) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

(h) The inspection and repair requirements shall be done in accordance with Boeing Service Bulletin 3477, dated July 26, 1990, or Boeing Service Bulletin 727-52-0142, dated July 26, 1990, as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C.

This amendment (39-8064, AD 91-22-04) becomes effective on November 29, 1991.

FOOTER: