AIRWORTHINESS DIRECTIVE

 

CAA-AD-015/2001

 

Date of issue: February 12, 2001

 

AIRCRAFT – FUEL QUANTITY INDICATING SYSTEM (FQIS) - INSPECTION

 

Applicability: All Model 737-300, -400, and -500 series airplanes; certificated in any category.

 

Effective date: February 28, 2001

 

Compliance: Required as indicated in FAA AD 2001-01-13.

 

Remarks: The compliance of this AD must be recorded in Aircraft Logbook, where applicable the requirements of this AD must be integrated into Aircraft Technical Documentation. Address inquiries concerning this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyne Airport, 160 08 Prague 6, Czech Republic, tel: 420 2 33320922, fax: 420 2 20562270.

 

Ing. Pavel MATOUŠEK
Director of Airworthiness Division
CAA CZ

 

2001-01-13 BOEING: Amendment 39-12084. Docket 2000-NM-313-AD.
Applicability: All Model 737-300, -400, and -500 series airplanes; certificated in any category.
NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 (e) 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.

Compliance: Required as indicated, unless accomplished previously.

To detect and correct chafing and to prevent electrical contact between the fuel quantity indicating system (FQIS) wiring and the surrounding structure, which, in conjunction with another wiring failure outside the fuel tank, could result in fire or explosion of the fuel tank, accomplish the following:

Compliance Plan

(a) Within 15 days after the effective date of this AD, submit a plan to the FAA that identifies a schedule for compliance with paragraph (b) of this AD. This schedule must include, for each of the operator's affected airplanes, the dates and maintenance events (e.g., letter checks) when the required actions will be accomplished. For purposes of this paragraph, "FAA" means the Principal Maintenance Inspector (PMI) for operators that are assigned a PMI, or the cognizant Flight Standards District Office for other operators. 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.

NOTE 2: Operators are not required to submit revisions to the compliance plan required by paragraph (a) of this AD to the FAA.

Inspection and Corrective Actions

NOTE 3: Repairs accomplished by splicing the wires in accordance with the procedure included in Boeing Alert Service Bulletin 737-28A1168, dated September 26, 2000, prior to the effective date of this AD, are considered acceptable for compliance with the requirements of paragraphs (b)(1), (b)(2), and (b)(3) of this AD.

(b) Except as provided by paragraph (c) of this AD: Within 6 months after the effective date of this AD, perform a one-time detailed visual inspection of the FQIS wiring and fuel tubing on the inboard side of the right wing rib wing buttock line (WBL) 227 and on the aft side of stringer No. 13 to determine if clearance of 3/8 inch or greater exists between the FQIS wire harness and the refuel tube and tube coupling, and to detect any loose or broken refuel tube clamp or bracket, or chafing of the FQIS wire harness, in accordance with Boeing Alert Service Bulletin 737-28A1168, Revision 1, dated January 11, 2001.

NOTE 4: For the purposes of this AD, a detailed visual inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required."

(1) If the clearance between the FQIS wire harness and the refuel tube is less than 3/8 inch, prior to further flight, readjust the refuel tube, and relocate the bonding jumper or lockwire away from the wiring, if necessary, in accordance with the service bulletin.

(2) If any loose or broken refuel tube clamp or bracket is found, prior to further flight, replace the broken clamp with a new clamp; repair the broken bracket or replace the broken bracket with a new bracket; and secure the loose clamp or bracket; as applicable; in accordance with the service bulletin.

(3) If any chafing of the FQIS wiring harness is found, prior to further flight, replace the wire harness with a new wire harness or accomplish the applicable action(s) specified in paragraph (b)(3)(i) or (b)(3)(ii) of this AD, in accordance with the service bulletin.

(i) For jacket damage only that is less than 1-inch in length with no sign of abrasion to the wire insulation: Install a teflon sleeve over the wiring. At the next scheduled "C" Check, but no later than 15 months after the effective of this AD, repair the wire harness or replace the wire harness with a new wire harness.

(ii) For jacket damage or a harness with an exposed shield or conductor and the insulation of the other wire is not damaged (there can be no broken shield strands if the shield wire is damaged or no broken wire strands if the unshielded wire is damaged): Install a teflon sleeve over the wiring terminal and along the wire to the damaged area.

(c) For airplanes on which the modification per AD 99-03-04, amendment 39-11018, has been accomplished prior to the effective date of this AD: Within 18 months after the effective date of this AD, perform the actions specified in paragraph (b), and in paragraph (b)(1) or (b)(2) of this AD, in accordance with Boeing Alert Service Bulletin 737-28A1168, Revision 1, dated January 11, 2001.

Reporting Requirement

(d) Submit a report of inspection findings to Service Bulletin Engineering, Boeing Commercial Airplane Group, P.O. Box 3707, Mail Stop 2H-37, Seattle, Washington 98124-2207; at the applicable time specified in paragraph (d)(1) or (d)(2) of this AD. The report must include all the information specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-28A1168, Revision 1, dated January 11, 2001. 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.

(1) For airplanes on which the inspection required by paragraph (b) of this AD is accomplished after the effective date of this AD: Submit the report within 10 days after performing the inspection.

(2) For airplanes on which the inspection required by paragraph (b) of this AD has been accomplished prior to the effective date of this AD: Submit the report within 10 days after the effective date of this AD.

Alternative Methods of Compliance
(e) 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, Seattle Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA PMI, who may add comments and then send it to the Manager, Seattle ACO.

NOTE 5: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.

Special Flight Permits

(f) Special flight permits may be issued in accordance with sections 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.

Incorporation by Reference

(g) Except for the requirements of paragraph (a) of this AD, the actions shall be done in accordance with Boeing Alert Service Bulletin 737-28A1168, Revision 1, dated January 11, 2001. 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 98124-2207. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

(h) This amendment becomes effective on February 28, 2001.

FOR FURTHER INFORMATION CONTACT: Sherry Vevea, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-1360; fax (425) 227-1181.

Issued in Renton, Washington, on January 11, 2001.

Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.