AD 99-01-13

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires modification of the airplane wiring to separate the electrical inputs sent by the engine interface units (EIU) to certain probe heat computers (PHC). This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent simultaneous loss of heating to pitot probes 1 and 3, which could result in incorrect airspeed indications to both the pilot s and first officer s airspeed indication systems. Malfunction of these systems could result in reduced controllability of the airplane.

Final rule.

99-01-13 AIRBUS INDUSTRIE: Amendment 39-10978. Docket 98-NM-07-AD.
Applicability: Model A319, A320, and A321 series airplanes; excluding airplanes on which Airbus Modification 26403 or Airbus Service Bulletin A320-30-1036, Revision 02, dated February 4, 1998, has 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 (b) 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 simultaneous loss of heating to pitot probes 1 and 3, which could result in incorrect airspeed indications to both the pilot's and first officer's airspeed indication systems, and reduced controllability of the airplane, accomplish the following:

(a) Within 6 months after the effective date of this AD, modify the airplane wiring to separate the electrical inputs sent by the engine interface units to probe heat computers 1 and 3, and test the modified wiring; in accordance with the service bulletin referenced in paragraph (a)(1) or (a)(2) of this AD, as applicable.

(1) For airplanes equipped with engines manufactured by CFM International (CFMI): Modify and test in accordance with Airbus Service Bulletin A320-30-1036, dated May 9, 1997; or Airbus Service Bulletin A320-30-1036, Revision 02, dated February 4, 1998.

NOTE 2:For airplanes equipped with CFMI engines: Accomplishment of the modification and test in accordance with Airbus Service Bulletin A320-30-1036, Revision 01, dated July 7, 1997, is considered acceptable for compliance with paragraph (a)(1) of this AD.

(2) For airplanes equipped with engines manufactured by International Aero Engines AG (IAE): Modify and test in accordance with Airbus Service Bulletin A320-30-1036, Revision 02, dated February 4, 1998.

NOTE 3: For airplanes equipped with IAE engines: Accomplishment of the modification in accordance with Airbus Service Bulletin A320-30-1036, dated May 9, 1997, or Revision 01, dated July 7, 1997, prior to the effective date of this AD, is considered acceptable for compliance with the modification specified by paragraph (a)(2) of this AD, provided that the modification is tested in accordance with the procedures specified in Airbus Service Bulletin A320-30-1036, Revision 02, dated February 4, 1998.

(b) 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 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

(c) 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.

(d) The modification and test shall be done in accordance with Airbus Service Bulletin A320-30-1036, dated May 9, 1997; or Airbus Service Bulletin A320-30-1036, Revision 02, dated February4, 1998, as applicable. 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 5: The subject of this AD is addressed in French airworthiness directives 97-203-102(B)R1 and 98-152-114(B), both dated April 8, 1998.

(e) This amendment becomes effective on February 12, 1999.

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 Model A319, A320, and A321 series airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on October 27, 1998 (63 FR 57263). That action proposed to require modification of the airplane wiring to separate the electrical inputs sent by the engine interface units (EIU) to certain probe heat computers (PHC).

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

All of the commenters support the proposed rule.

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

Cost ImpactThe FAA estimates that 150 airplanes of U.S. registry will be affected by this AD.

It will take approximately 3 work hours per airplane to accomplish the required modification (including testing), at an average labor rate of $60 per work hour. Required parts will be provided by the manufacturer at no cost to the operators. Based on these figures, the cost impact of this AD on U.S. operators is estimated to be $27,000, or $180 per airplane.

Should an operator be required to re-test modified wiring, it will take approximately 1 additional work hour per airplane to accomplish the test, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of any necessary re-test required by this AD on U.S. operators is estimated to be $60 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: