AD 2001-15-02 Airworthiness Directives; Boeing Model 747 Series Airplanes Powered By Pratt & Whitney JT9D-3 and -7 Series Engines

Models named: 747 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 747 series airplanes, certificated in any category, as listed in Boeing Alert Service Bulletin 747-54A2203, dated August 31, 2000; except Model 747 series airplanes having serial numbers 21048 and 20887. 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 (d)(1) 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 loose fasteners and associated damage to the hanger fittings and strut forward bulkhead of the forward engine mount, which could result in separation of the engine from the airplane, accomplish the following: Restatement of Requirements of AD 2000-23-16 Repetitive Inspections/Checks (a) Within 60 days after December 6, 2000 (the effective date of AD 2000-23-16, amendment 39-11988): Perform a detailed visual inspection and torque check as specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2203, dated August 31, 2000, to detect loose fasteners and associated damage to the hanger fittings and bulkhead of the forward engine mount, in accordance with Figure 1 of the alert service bulletin. Note 2: 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 no loose fastener or associated damage is detected, repeat the inspections/checks thereafter at the applicable intervals specified in Figure 1 of the alert service bulletin until accomplishment of the terminating action specified in paragraph (c) of this AD. Note 3: Where there are differences between the AD and the alert service bulletin, the AD prevails. Corrective Actions (2) If any loose fastener or associated damage is detected, before further flight, perform the applicable corrective actions (torque check, rework or replacement of fittings), as specified in Figure 1 of the alert service bulletin. Repeat the inspections/checks thereafter at the applicable intervals specified in Figure 1 of the alert service bulletin until accomplishment of the terminating action specified in paragraph (c) of this AD. Where the alert service bulletin specifies that the manufacturer may be contacted for disposition of certain corrective actions (rework or replacement of fittings), this AD requires such rework and/or replacement to be done in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or in accordance with data meeting the type certification basis of the airplane approved by a Boeing Company designated engineering representative (DER) who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD. New Requirements of this AD Repetitive Checks/ Inspections/Corrective Actions (b) Within 18 months after the effective date of this AD: Do the torque check specified in Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2203, dated August 31, 2000, to detect loose fasteners of the hanger fittings of the forward engine mount. (1) If no loose fastener is detected, repeat the torque check thereafter at intervals not to exceed 1,200 flight cycles or 18 months, whichever occurs first, until accomplishment of the terminating action specified in paragraph (c) of this AD. (2) If any loose fastener is detected, before further flight, perform the applicable corrective actions as specified in Figure 4, Figure 5, or Part 6, as applicable, of the Accomplishment Instructions of the alert service bulletin. (i) If Figure 4 or Figure 5 of the Accomplishment Instructions of the alert service bulletin is used to do the corrective actions for the fitting; thereafter, repeat the detailed visual inspection required by paragraph (a) of this AD at the applicable intervals specified in Figure 1 of the alert service bulletin, and repeat the torque check for that fitting at intervals not to exceed 180 flight cycles. Accomplish the terminating action for that fitting as specified in Part 6 of the Accomplishment Instructions of the alert service bulletin within 18 months after finding any loose fastener or 60 months after the effective date of this AD, whichever occurs first. (ii) If Part 6 of the Accomplishment Instructions of the alert service bulletin is used to do the corrective actions for the fitting, this constitutes terminating action for the repetitive inspections/checks for that fitting only. (3) If any associated damage is found, before further flight, repair in accordance with a method approved by the Manager, Seattle ACO, or in accordance with data meeting the type certification basis of the airplane approved by a Boeing Company DER who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD. If any damage to any fitting is found, before further flight, do the applicable corrective actions specified in Part 4 or Part 5 of the Accomplishment Instructions of the alert service bulletin; this constitutes terminating action for the repetitive inspections/checks for that fitting only. (4) If any loose fastener is detected during any repeat inspection/check specified in paragraph (b)(2)(i) of this AD, before further flight, accomplish the terminating action for that fitting as specified in Part 6 of the Accomplishment Instructions of the alert service bulletin. Terminating Action (c) Within 60 months after the effective date of this AD: Accomplish all actions in the terminating action specified in Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2203, dated August 31, 2000. Accomplishment of this paragraph constitutes terminating action for the repetitive inspections/checks required by paragraphs (a) and (b) of this AD. Where the alert service bulletin specifies that the manufacturer may be contacted for disposition of certain corrective actions (rework or replacement of fittings), this AD requires such rework and/or replacement to be done in accordance with a method approved by the Manager, Seattle ACO; or in accordance with data meeting the type certification basis of the airplane approved by a Boeing Company DER who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD. Note 4: Installation of two BACW10BP*APU washers on Group A fasteners accomplished during modification in accordance with Boeing Service Bulletin 747-54A2159, dated November 3, 1994, Revision 1, dated June 1, 1995, or Revision 2, dated March 14, 1996; and pin or bolt protrusion as specified in the 747 Structural Repair Manual, Chapter 51-30-02 (both referenced in Boeing Alert Service Bulletin 747-54A2203, dated August 31, 2000); is considered acceptable for compliance with the terminating action specified in paragraph (c) of this AD. Alternative Methods of Compliance (d)(1) 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 ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. (2) Alternative methods of compliance, approved previously in accordance with AD 2000-23-16, amendment 39-11988, are approved as alternative methods of compliance for corresponding actions in this AD. 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 (e) 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 (f) Except as provided by paragraph (a)(2), (b)(3), and (c) of this AD, the actions shall be done in accordance with Boeing Alert Service Bulletin 747-54A2203, dated August 31, 2000. The incorporation by reference of that document was approved previously by the Director of the Federal Register as of December 6, 2000 (65 FR 69862, November 21, 2000). Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. 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 (g) This amendment becomes effective on August 24, 2001. Issued in Renton, Washington, on July 13, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-18138 Filed 7-19-01; 8:45 am] BILLING CODE 4910-13-P