AD 97-02-01

This amendment adopts a new airworthiness directive (AD) that applies to The New Piper Aircraft, Inc. (Piper) Model PA-31T2 airplanes that have a Parker Hannifin Wheel and Brake Conversion Kit 199-111 installed in accordance with Supplemental Type Certificate (STC) SA599GL. This action requires rerouting the landing gear emergency extension line. This AD results from three incidents of the brake cylinder contacting the landing gear emergency extension air line on both wheel wells. The actions specified by this AD are intended to prevent the brake cylinder from chafing against the landing gear emergency extension air line when the gear is in the up and locked position, which could result in damage to the air line and subsequent loss of emergency gear extension capability.

Final rule

97-02-01 THE NEW PIPER AIRCRAFT, INC.: Amendment 39-9885; Docket No. 95-CE- 21-AD.

Applicability: Model PA31T2 airplanes (serial numbers 31T-8166001 through 31T-8166062), certificated in any category, that have a Parker Hannifin Wheel and Brake Conversion Kit 199-111 incorporated in accordance with Supplemental Type Certificate (STC) SA599GL.

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 (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 conditionhas not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished.

To prevent the brake cylinder from chafing against the landing gear emergency extension air line when the gear is in the up and locked position, which could result in damage to the air line and subsequent loss of emergency gear extension capability, accomplish the following:

(a) Reroute the landing gear emergency extension air line in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Parker Hannifin Service Bulletin SB7034, Revision B, dated December 19, 1995.

(b) 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.

(c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Chicago Aircraft Certification Office (ACO), FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Chicago ACO.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Chicago ACO.

(d) The rerouting required by this AD shall be done in accordance with Parker Hannifin Service Bulletin SB7034, Revision B, dated December 19, 1995. 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 the Parker Hannifin Corporation, Aircraft Wheel & Brake, 1160 Center Road, P.O. Box 158, Avon, Ohio 44011. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(e) This amendment becomes effective on February 14, 1997.

Events Leading to This Action
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to Piper Model PA-31T2 airplanes that have a Parker Hannifin Wheel and Brake Conversion Kit 199-111 installed in accordance with STC SA599GL was published in the Federal Register on June 13, 1996 (61 FR 29992). The action proposed to require rerouting the landing gear emergency extension air line. Accomplishment of the proposed action as specified in the supplemental notice of proposed rulemaking (NPRM) would be in accordance with Parker Hannifin Service Bulletin SB7034, Revision B, dated December 19, 1995.

The supplemental NPRM results from three incidents of the brake cylinder contacting the landing gear emergency extension air line on both wheels.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposed rule or theFAA's determination of the cost to the public.

The FAA's Determination
After careful review of all available information related to the subject presented above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed except for minor editorial corrections. The FAA has determined that these minor corrections will not change the meaning of the AD and will not add any additional burden upon the public than was already proposed.

Cost Impact
The FAA estimates that 62 Piper Model PA31-T2 airplanes in the U.S. registry could incorporate Parker Hannifin Wheel and Brake Conversion Kit 199-111 (in accordance with STC SA599GL), that it will take approximately 4 workhours per airplane to accomplish the required action, and that the average labor rate is approximately $60 an hour. Parts cost approximately $20 per airplane. Based on these figures, the total cost impact of the AD on U.S. operators could be as much as $16,120 if all affected airplanes had the referenced conversion kit installed.

Parker Hannifin has informed the FAA that it has distributed 31 kits (shipped after March 28, 1994) to Piper Model PA31T2 airplane owners/operators. Kits shipped after March 28, 1994, included the replacement parts referenced in Parker Hannifin SB7034, Revision B, dated December 19, 1995. Based on each of the 31 kits being incorporated on an affected airplane, the cost impact of this AD on U.S. owners and operators is reduced 50 percent from $16,120 to $8,060. The reduction results from the difference between the 62 airplanes that are type certificated to have a Parker Hannifin Wheel and Brake Conversion Kit 199-111 incorporated (in accordance with STC SA599GL) and the 31 kits that have already been distributed.

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 powerand 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 copy of the final 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, 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 USC 106(g), 40113, 44701.

39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows: