AD 96-07-11 ACTIVE

This amendment adopts a new airworthiness directive (AD), applicable to all Beech Model BAe 125-1000A and Hawker 1000 series airplanes, that requires a detailed visual inspection to detect chafing damage to the hydraulic pipes adjacent to the hydraulic module, and various follow-on actions. This amendment is prompted by reports of chafing damage between hydraulic pipes at three locations in the rear equipment bay adjacent to the hydraulic module. The actions specified by this AD are intended to prevent such chafing damage to the hydraulic pipe and subsequent hydraulic fluid leakage, which could lead to failure of essential airplane systems.

Final rule.

96-07-11 BEECH AIRCRAFT CORPORATION (Raytheon Aircraft Company) (Formerly DeHavilland; Hawker Siddeley; British Aerospace, plc; Raytheon Corporate Jets, Inc.): Amendment 39-9560. Docket 95-NM-141-AD.

Applicability: All Model BAe 125-1000A and Hawker 1000 series airplanes, certificated in any category.

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 (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 chafing damage to the hydraulic pipe and subsequent hydraulic fluid leakage; this condition may lead to failure of essential airplane systems, accomplish the following:

(a) Within 3 months after the effective date of this AD, perform a detailed visual inspection to detect chafing damage to the hydraulic pipes located aft of frame 21 and adjacent to the hydraulic module, in accordance with Hawker Service Bulletin SB.29-95, dated March 24, 1995.

(1) If no chafing damage is detected, prior to further flight, perform a visual inspection to determine if adequate clearance exists between the intersecting pipe runs, and between pipes and adjacent equipment or structure, in accordance with the service bulletin.

(i) If the clearance is adequate, no further action is required by this AD.

(ii) If the clearance is inadequate, prior tofurther flight, adjust the pipe connections and/or clipping to restore adequate clearance, in accordance with the service bulletin.

(iii) If any chafing damage to other equipment or structure is found, prior to further flight, repair it in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(2) If any chafing damage is detected and it is beyond the limits specified in paragraph 2.B.(4) of the service bulletin, prior to further flight, replace the damaged pipe with a new pipe in accordance with the service bulletin.

(3) If any chafing damage is detected within the limits specified in paragraph 2.B.(4) of the service bulletin, prior to further flight, perform a pressure test or replace the damaged pipe with a new pipe in accordance with the service bulletin.

(i) If the pipes are satisfactory, no further action is required by this AD.

(ii) If any pipe leaks and/or if any distortion occursin or around the area of chafing damage, prior to further flight, replace the pipe with a new pipe in accordance with the service bulletin.

(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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

(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) Theactions shall be done in accordance with Hawker Service Bulletin SB.29-95, dated March 24, 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 Beech Aircraft Corporation, Manager Service Engineering, Hawker Customer Support Department, P.O. Box 85, Wichita, Kansas 67201-0085. 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.

(e) This amendment becomes effective on May 6, 1996.

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 all Beech Model BAe 125-1000A and Hawker 1000 series airplanes was published in the Federal Register on December 19, 1995 (60 FR 65254). That action proposed to require a detailed visual inspection to detect chafing damage to the hydraulic pipes located aft of frame 21 and adjacent to the hydraulic module, and various follow-on actions (i.e., visual inspection, adjustment, replacement, pressure test).

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that 27 airplanes of U.S. registry will be affected by this AD, that itwill take approximately 1 work hour per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $1,620, or $60 per airplane.

The cost impact figure discussed above is 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.

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 USC 106(g), 40113, 44701.

39.13 - [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive:

The service information referenced in this AD may be obtained from Beech Aircraft Corporation, Manager Service Engineering, Hawker Customer Support Department, P.O. Box 85, Wichita, Kansas 67201-0085. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Tim Backman, Aerospace Engineer, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 227-2797; fax (206) 227-1149.