AD 98-01-12

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A320 series airplanes, that requires an inspection to detect moisture and migrated bushings of the guide fittings of the safety locking pins of the passenger doors, removal of any moisture, application of grease, and reinstallation of any migrated bushing. This amendment also requires installation of a greasing nipple on the guide fitting of the locking pin and on three telescopic rods on the passenger doors. This amendment is prompted by reports of difficulty opening the passenger doors due to jamming of the locking pin. The actions specified by this AD are intended to prevent such jamming of the locking pin, which could result in inability to open the passenger door. This condition, if not corrected, could impede or delay passengers from exiting the airplane during an emergency.

Final rule.

98-01-12 AIRBUS INDUSTRIE: Amendment 39-10275. Docket 95-NM-90-AD.

Applicability: Model A320 series airplanes on which Airbus Industrie Modification No. 24389 (Airbus Industrie Service Bulletin No. A320-52-1057, dated July 26, 1994) has not been accomplished, 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 (c) 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 prevent jamming of the upper safety locking pin on the passenger door, which could result in inability to open the passenger door and, consequently, could impede or delay passengers from exiting the airplane during an emergency, accomplish the following:

(a) Prior to the accumulation of 450 hours time-in-service after one year from the delivery date of the airplane, or within 450 hours time-in-service after the effective date of this AD, whichever occurs later: Perform an inspection to detect moisture or migrated bushings of the guide fittings of the upper safety locking pins on each passenger door, in accordance with Airbus Industrie All Operators Telex (AOT) 52-06, dated February 4, 1994.

(1) If any moisture is found in the guide fitting, prior to further flight, remove the moisture, dry the guide fitting, fill it with low temperature grease, and reinstall the guide fitting with bolts, washers, and nuts in accordance with the AOT.

(2) If any migrated bushing is found, prior to further flight, reinstall the bushing using Loctite 672 in accordance with the AOT. If the bushing cannot be reinstalled prior to further flight, the airplane may be operated without the upper locking pin for an additional 50 hours time-in-service or three days after accomplishing the inspection, whichever occurs first, provided that the requirements specified in paragraphs (a)(2)(i), (a)(2)(ii), and (a)(2)(iii) of this AD are accomplished. This compliance time applies to each passenger door.

(i) The connecting rod to the locking shaft shall be removed.

(ii) The guide fitting shall remain installed.

(iii) The cavity in the guide fitting (which results from the removal of the upper locking pin) shall be covered with high speed tape to prevent moisture ingress.

(b) Within 15 months after the effective date of this AD, install a greasing nipple on the guide fitting of the locking pin and on three telescopic rods on the passenger doors in accordance with Airbus Industrie Service Bulletin No. A320-52-1057, dated July 26, 1994.

(c) 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, International Branch, ANM-116, FAA, Transport 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, International Branch, ANM-116.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

(d) 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.

(e) The actions shall be done in accordance with Airbus Industrie All Operators Telex (AOT) 52-06, dated February 4, 1994, and Airbus Industrie Service Bulletin No. A320-52-1057, dated July 26, 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 may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 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.

NOTE 3: The subject of this AD is addressed in French airworthiness directive 94-239- 060(B), dated November 9, 1994.

(f) This amendment becomes effective on February 17, 1998.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Airbus Industrie Model A320 series airplanes was published in the Federal Register on November 3, 1995 (60 FR 55811). That action proposed to require a one-time inspection to detect moisture and migrated bushings of the guide fittings of the upper safety locking pins of the passenger doors, removal of any moisture, application of grease, and reinstallation of any migrated bushing. That action also proposed to require installation of a greasing nipple on the guide fitting of the locking pin and on three telescopic rods on the passenger doors.

Comments
Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received.

Request to Extend Compliance Time for Installation of Greasing Nipple
One commenter requests that the compliance time for accomplishing the proposed installation of a greasing nipple on the three telescopic rods on the passenger door be extended from the proposed 15 months to 18 months. The commenter states that such an extension will allow the installation to be accomplished during a regularly scheduled "C" check, and thereby eliminate any expenses that would be associated with special scheduling. Another commenter requests an explanation as to how the 15-month compliance time was established.

The FAA does not concur with the commenter s request to extend the compliance time. In developing an appropriate compliance time for this action, the FAA considered the safety implications, parts availability, and normal maintenance schedules for timely accomplishment of the installation. Further, the proposed compliance time of 15 months was arrived with operator, manufacturer, Direction G n rale de l'Aviation Civile (DGAC) (the airworthiness authority for France), and FAAconcurrence. In light of this, and in consideration of the amount of time that has already passed since issuance of the original notice, the FAA has determined that further delay of this final rule is not appropriate. However, under the provisions of paragraph (c) of the final rule, the FAA may approve requests for adjustments to the compliance time if data are submitted to substantiate that such an adjustment would provide an acceptable level of safety.

Request to Require Only Rework of Safety Guide Pin Fitting
One commenter requests that the proposed AD be revised to require only rework applicable to the telescopic rods of the passenger door if Airbus Industrie Service Bulletin A320-52-1030 has not been accomplished. (The proposal requires that actions be accomplished in accordance with Airbus Industries Service Bulletin A320-52-1057.) The commenter points out that the sliding arming mechanism telescopic rod has been the subject of Airbus Industrie Service Bulletin A320-52-1030, which describes procedures to detect a corrosion problem. Since incorporation of that service bulletin, the commenter states that it has not had any discrepancies with any of the telescopic rods that are subject to the proposed AD. The FAA does not concur. The FAA finds that the procedures specified in Airbus Industrie Service Bulletin A320-52-1030 do not address the same unsafe condition addressed by this AD (i.e., jamming of the locking pin). The FAA has determined that accomplishment of the procedures specified in Airbus Industrie Service Bulletin A320-52-1057, as proposed, adequately addresses the identified unsafe condition by preventing jamming of the locking pin. However, under the provisions of paragraph (c) of this AD, operators may apply for the approval of an alternative method of compliance, if sufficient justification is presented to the FAA.

Conclusion
After careful review of the available data, including the comments noted above, the FAA has determined thatair safety and the public interest require the adoption of the rule as proposed.

Cost Impact
The FAA estimates that 108 airplanes of U.S. registry will be affected by this AD, that it will take approximately 4 work hours per airplane (1 work hour per door; 4 doors per airplane) to accomplish the required inspection, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the inspection required by this AD on U.S. operators is estimated to be $25,920, or $240 per airplane.

The FAA estimates that it will take approximately 40 work hours per airplane to accomplished the required installation, and that the average labor rate is $60 per work hour. Required parts will be supplied by the manufacturer at no cost to operators. Based on these figures, the cost impact of the installation on U.S. operators is estimated to be $259,200, or $2,400 per airplane.

The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted.

Regulatory Impact
The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: