AD 96-16-08 Airworthiness Directives; Boeing Model 727-100 and -200 Series Airplanes With a Main Deck Cargo Door Installed in Accordance With Supplemental Type Certificate (STC) SA1797SO

Models named: 727-100, -200 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 727-100 and -200 series airplanes that have been modified in accordance with Supplemental Type Certificate (STC) SA1797SO, certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. -To prevent the inadvertent opening of the main deck cargo door during flight, which could result in major structural damage and possible reduced controllability of the airplane, accomplish the following: -(a) Accomplish the actions specified in paragraphs (a)(1), (a)(2), (a)(3), and (a)(4) of this AD at the time specified in each of those paragraphs: -(1) Within 3 days after the effective date of this AD, perform a visual inspection of internal wires and electrical components of the control box of the main deck cargo door to detect the following discrepancies: -(i) chafed, crimped, crushed, or damaged electrical wires or wire bundles inside the control box of the cargo door; -(ii) loose electrical wire connections; -(iii) abnormally pulled or twisted individual wires or wire bundles; -(iv) any removal of insulation from the conductor in the control box; or -(v) any damaged protective grommets. [[Page 41735]] (2) If any discrepancy is detected during the inspection required by paragraph (a)(1) of this AD, prior to further flight, repair it in accordance with a method approved by the Manager, FAA, Atlanta Aircraft Certification Office (ACO), Small Airplane Directorate. (3) Following accomplishment of paragraphs (a)(1) and, if applicable, (a)(2) of this AD, verify that the wire and wire bundles are properly installed and restrained, and reinstall and restrain any wire or component that has been altered, in accordance with the document identified in either paragraph (a)(3)(i) or (a)(3)(ii) of this AD. (i) Section 1 (``Care of Electrical System''); Section 3 (``Electric Wire''); Section 5 (``Connectors''); and Section 7 (``Routing, Tying, Lacing, and Clamping); of Chapter 11 (``Electrical Systems'') of FAA Advisory Circular AC 4313-1A, Change 3, dated 1988; or (ii) Chapter 20 (``Standard Wiring Practices'') of Boeing Wiring Diagram Manual Document D6-54446, Revision 21, dated June 1, 1994. (4) Within 10 days after accomplishing the inspection required by paragraph (a)(1) of this AD, submit a report of the inspection results (both positive and negative findings) to the Manager, FAA, Atlanta Aircraft Certification Office, Small Airplane Directorate, Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia 30337-2748; telephone (404) 305-7381; fax (404) 305-7348. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120- 0056. (b) Within 3 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM. ``Operational Restriction Prior to taxi, verify that the alternating current (AC) or direct current (DC) circuit breakers that supply electrical power to the hydraulic pump motor are PULLED to interrupt power to the motor pump power relay and pump motor. Note 1: The 28VDC circuit breaker is located in the electrical equipment compartment on the J9 battery shield panel next to the auxiliary power unit (APU) starter circuit breaker. The 115VAC circuit breakers are located on the P6 breaker panel to the right of the Flight Engineers station. These circuit breakers are identified as ``Cargo Door Hydraulic Pump''. Prior to each taxi and take-off after closing the cargo door, set these circuit breakers to an open condition. Tag and secure the circuit breakers for flight. After landing and taxiing to the ramp, the circuit breakers may be RESET to facilitate cargo door opening.'' (c) Within 90 days after the effective date of this AD, modify the wiring and components of the control box of the main deck cargo door, in accordance with a method approved by the Manager, FAA, Atlanta Aircraft Certification Office (ACO), Small Airplane Directorate. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, FAA, Atlanta Aircraft Certification Office (ACO), Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (e) Special flight permits may be issued in accordance with 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) Certain actions shall be done either in accordance with Sections 1, 3, 5, and 7 of Chapter 11 (``Electrical Systems'') of FAA Advisory Circular (AC) 4313-1A, Change 3, dated 1988; or in accordance with Chapter 20 (``Standard Wiring Practices'') of Boeing Wiring Diagram Manual Document D6-54446, Revision 21, dated June 1, 1994. Sections 1, 3, 5, and 7 of Chapter 11 of FAA Advisory Circular AC 4313-1A contain the following list of effective pages: ---------------------------------------------------------------------------------------------------------------- Date shown on Section referenced- Page number- Change level shown on page- page ---------------------------------------------------------------------------------------------------------------- Section 1, ``Care of Electrical 173-174-................ Original-.................... 1972 Systems''. Section 3, ``Electric ``Wire''---..... 179, 180, 180-1,180-2, 3............................ 1988 181, 181-1, 181-2, 182, 182-1, 182-2, 183-185, 185-1, 185-2, 186, 188, 188-1, 188-2. 187, 189-193-........... Original-.................... 1972 Section 5, ``Connectors''-............ 196,200-................ 3-........................... 1988 197-199................. Original..................... 1972 Section 7, ``Routing,Tying, Lacing, 203, 204, 206-209-...... Original..................... 1972 and Clamping''-. - 205, 205-1, 205-2....... 3-........................... 1988 ---------------------------------------------------------------------------------------------------------------- -Chapter 20 of Boeing Wiring Diagram Manual Document D6-54446 contains the following list of effective pages: ------------------------------------------------------------------------ Page title and number Date shown on page ------------------------------------------------------------------------ Title Page-.......................... December 1, 1991. Revision Transmittal Pages 1-6....... June 1, 1994. Revision Record Pages 1, 2-.......... December 1, 1991. Temporary Revision Record Pages 1, 2 - December 1, 1991. . List of Effective Pages 1-30......... June 1, 1994. ------------------------------------------------------------------------ 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 of Boeing Manufacturing Drawing D65446 may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies of FAA Advisory Circular (AC) 4313-1A may be obtained from Superintendent of Documents, U.S. Government Printing Office, Washington, DC 20402. Copies of all of these documents may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at FAA, Atlanta Aircraft Certification Office, Small Airplane Directorate, Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia 30337-2748; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on August 27, 1996. Issued in Renton, Washington, on August 2, 1996. Gary L. Killion, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 96-20307 Filed 8-9-96; 8:45 am] BILLING CODE 4910-13-U