AD 2005-07-18 Airworthiness Directives; McDonnell Douglas Model DC-9-15F Airplanes Modified In Accordance With Supplemental Type Certificate (STC) SA1993SO; and Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes in All-Cargo Configuration, Equipped With a Main-Deck Cargo Door

Models named: DC-9-15F. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to McDonnell Douglas Model DC-9-15F airplanes modified in accordance with supplemental type certificate (STC) SA1993SO; and Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, DC-9-15F, DC-9-21, DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, and DC-9-51 airplanes in all-cargo configuration, equipped with a main-deck cargo door; certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Airplanes Not Modified in Accordance With STC SA1993SO: Inspection and Reporting (f) For airplanes not modified in accordance with STC SA1993SO: Within 60 days after the effective date of this AD, perform an inspection of the main deck cargo compartment to determine the details of the airplane's cargo configuration. Within 60 days after the effective date of this AD, submit a report of the details of the airplane's cargo configuration through the FAA Principal Maintenance Inspector (PMI), or the cognizant Flight Standards District Office, as applicable, to the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. The report must include the airplane serial number, inspection results, and the information specified in paragraphs (f)(1), (f)(2), (f)(3), and (f)(4) of this AD. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056. (1) Restraint system: Does the airplane have vertical side restraints installed on the main deck floor? How many vertical side restraints are installed per airplane side? (2) Vertical fore/aft restraints: How many vertical fore/aft restraints are installed on each end of a pallet position? (3) For airplanes with missing vertical side restraints: Is a bump rail installed? (4) Unit Loading Devices (ULDs): What type/model ULDs are used for cargo carriage in affected airplanes? Obtain NAS 3610 designation from affixed data plate as required by Technical Standard Order (TSO) C90a, b, c, or designation provided by STC or other approved means. Is there a manual or document that indicates the type/model of ULDs to use? If there is such a manual or document, include the manual/document number and revision level in the report required by paragraph (f) of this AD. Airplanes Deviating From Original Configuration: Required Action (g) During the inspection required by paragraph (f) of this AD, if the airplane's cargo configuration deviates from the original configuration as delivered by McDonnell Douglas (including, but not limited to, missing vertical side restraints or revised fore/aft restraint configuration), accomplish paragraphs (h) and (i) of this AD. Manual Revisions (h) For airplanes modified in accordance with STC SA1993SO and airplanes specified in paragraph (g) of this AD: Within 90 days after the effective date of this AD, revise the Limitations section of the airplane flight manual (AFM), the AFM supplements, the Limitations section of the airplane weight and balance manual (AWBM), and the AWBM supplements to include the information specified below. This may be accomplished by inserting a copy of this AD into the affected manual or supplement. After accomplishment of these revisions, the airplane must be operated in accordance with these limitations. “REDUCTION IN CARGO LOADS AS FOLLOWS: • Zone 1 (most forward): Limited to a maximum of 4,000 pounds, • Zones 2 through 7: Limited to a maximum of 5,200 pounds each, • Zone 8 (most aft): Limited to a maximum of 2,000 pounds. Note: The maximum total payload that can be carried on the main deck is limited to the lesser of: • The approved cargo barrier weight limit, • Weight permitted by the approved maximum zero-fuel weight, • Weight permitted by the approved main deck position weights, • Weight permitted by the approved main deck running load or distributed load limitations, or • Approved cumulative zone or fuselage monocoque structural loading limitations (including lower hold cargo). Limitations: Use only unit loading devices (ULDs) (containers and pallets) that are structurally compatible with the cargo loading system. One means of establishing compatibility is through compliance with the specifications of NAS 3610 for ULDs approved under Technical Standard Order (TSO) C90a, b, or c; or as provided by the appropriate instructions of a Supplemental Type Certificate or other approved means. Alternative methods of compliance can be obtained as specified in paragraph (j) of this AD. Ensure proper restraining of the ULDs by engaging all cargo loading system restraints. The center-of-gravity shift of each ULD must not exceed 10 percent of its base longitudinal or lateral directions. Relocation of Cargo Restraints (i) For airplanes modified in accordance with STC SA1993SO and airplanes specified in paragraph (g) of this AD: Within 90 days after the effective date of this AD, relocate all fore/aft cargo restraints in the main cargo deck to left and right buttock lines 22.0 and 44.5. Alternative Methods of Compliance (AMOCs) (j) The Manager, Atlanta ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Material Incorporated by Reference (k) None. Issued in Renton, Washington, on March 25, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-6757 Filed 4-5-05; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by reports that deficiencies related to the cargo loading system may exist on all McDonnell Douglas Model DC-9-15F airplanes modified in accordance with STC SA1993SO. We are issuing this AD to ensure that cargo in the main cabin is adequately restrained and to prevent failure of components of the cargo loading system, failure of the floor structure, or shifting of cargo. Any of these conditions could cause cargo to exceed load distribution limits or cause damage to the fuselage or control cables, which could result in reduced controllability of the airplane.