01-10346. Airworthiness Directives; Aerospatiale Model ATR72-101, -201, -102, -202, -211, and -212 Series Airplanes

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

This document proposes the adoption of a new airworthiness directive (AD) that is applicable to certain Aerospatiale Model ATR72-101, -201, -102, -202, -211, and -212 series airplanes. This proposal would require replacement of the clamp retaining the power supply cable loom of the green circuit hydraulic pump at frame 28 with a smaller clamp in a different orientation. This action is necessary to prevent the chafing of electrical wires, which could cause a short circuit and failure of the elevator control cable and the green system hydraulic pump, resulting in reduced controllability of the airplane and consequent injury to the crew and passengers. This action is intended to address the identified unsafe condition.

DATES:

Comments must be received by May 29, 2001.

ADDRESSES:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2001-NM-38-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal holidays. Comments may be submitted via fax to [phone]. Comments may also be sent via the Internet using the following address: [e-mail]. Comments sent via fax or the Internet must contain “Docket No. 2001-NM-38-AD” in the subject line and need not be submitted in triplicate. Comments sent via the Internet as attached electronic files must be formatted in Microsoft Word 97 for Windows or ASCII text.

The service information referenced in the proposed rule may be obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Todd Thompson, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone [phone]; fax [phone].

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of the proposed rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this action may be changed in light of the comments received.

Submit comments using the following format:

• Organize comments issue-by-issue. For example, discuss a request to change the compliance time and a request to change the service bulletin reference as two separate issues.
• For each issue, state what specific change to the proposed AD is being requested.
• Include justification (e.g., reasons or data) for each request.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report summarizing each FAA-public contact concerned with the substance of this proposal will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this action must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket Number 2001-NM-38-AD.” The postcard will be date stamped and returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2001-NM-38-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

Discussion

The Direction Générale de l'Aviation Civile (DGAC), which is the airworthiness authority for, notified the FAA that an unsafe condition may exist on certain Aerospatiale Model ATR72-101, -201, -102, -202, -211, and -212 series airplanes. The DGAC advises that Model ATR72-202 series airplane, while taxiing out, experienced an elevator pitch disconnect; a loss of the green system hydraulic pump; and eruption of a small fire. Investigations revealed that the power supply cables of the green system hydraulic pump had chafed on the right-hand elevator control cable, between frames 28 and 28A. This chafing led to a short circuit, which caused the elevator control cable to snap and the hydraulic pump power supply circuit breaker to trip. The heat generated started a small fire, which extinguished itself.

It was determined that the chafing and subsequent electrical short circuit were caused by the installation of an oversized clamp (diameter 20 mm) on the power supply cables loom (diameter 16 mm) of the green system hydraulic pump. The larger clamp gave the cables freedom to move and did not secure wiring conduit 2P in the forward area, where the cables loom changes direction. This condition, if not corrected, could cause the chafing of electrical wires, and consequent short circuit, snapping of the elevator control cable, tripping of the hydraulic pump power supply circuit breaker, and possible fire, resulting in reduced controllability of the airplane and consequent injury to the crew and passengers.

Explanation of Relevant Service Information

Aerospatiale has issued Avions de Transport Regional Service Bulletin ATR72-92-1004, dated January 26, 2001, which describes procedures for a one-time inspection of harness route 2P and the pitch control cable for wire chafing, corrective action, if necessary, and replacement of the 20 mm clamp with a 16 mm clamp in a rotated position. Accomplishment of the actions specified in the service bulletin is intended to adequately address the identified unsafe condition. The DGAC classified this service bulletin as mandatory and issued French airworthiness directive 2001-056-055(B), dated February 7, 2001, in order to assure the continued airworthiness of these airplanes in France.

FAA's Conclusions

These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, the proposed AD would require accomplishment of the actions specified in the service bulletin described previously.

Cost Impact

The FAA estimates that 60 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 1 work hour per airplane to accomplish the proposed replacement, and that the average labor rate is $60 per work hour. Required parts would be supplied by the manufacturer at no cost to the operators. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $3,600, or $60 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the proposed requirements of this AD action, and that no operator would accomplish those actions in the future if this proposed AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.

Regulatory Impact

The regulations proposed herein would not have a substantial direct effect 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, it is determined that this proposal would not have federalism implications under Executive Order 13132.

For the reasons discussed above, I certify that this proposed regulation (1) is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, 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 copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• Safety

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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:

Aerospatiale: Docket 2001-NM-38-AD.

Applicability: Model ATR72-101, -201, -102, -202, -211, and -212 series airplanes, certificated in any category, except those on which Modification 3719 has been performed.

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 the chafing of electrical wires, which could cause a short circuit and failure of the elevator control cable and the green system hydraulic pump, resulting in reduced controllability of the airplane and consequent injury to the crew and passengers, accomplish the following:

Inspection and Corrective Action

(a) Within 25 days after the effective date of this AD: Perform a general visual inspection of harness route 2P and the pitch control cable for chafing, in accordance with Avions de Transport Regional Service Bulletin ATR72-92-1004, dated January 26, 2001.

(1) If no chafing is found, no further action is required by this paragraph.

(2) If any chafing of the harness route 2P or the pitch control cable is found during the inspection, prior to further flight, replace the applicable part with a new or serviceable part in accordance with Avions de Transport Regional Service Bulletin ATR72-92-1004, dated January 26, 2001.

Note 2:

For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light, and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”

(b) Within 25 days after the effective date of this AD: Remove the oversized clamp (20 mm), part number (P/N) NSA935807-20, at frame 28, which retains power supply cables loom 2P for the green circuit hydraulic pump, and install a 16mm clamp, P/N NSA935807-16, with new orientation, in accordance with Avions de Transport Regional Service Bulletin ATR72-92-1004, dated January 26, 2001.

Alternative Methods of Compliance

(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, Transport Airplane Directorate, FAA. 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 3:

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

Special Flight Permits

(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.

Note 4:

The subject of this AD is addressed in French airworthiness directive 2001-056-055(B), dated February 7, 2001.

Issued in Renton, Washington, on April 19, 2001.

Donald L. Riggin,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.