AD 96-11-17

This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe 125 series 1000A and Model Hawker 1000 airplanes, that requires a one-time inspection for adequate clearances between, and damage to, the flap cables and turnbuckles, airbrakes cables and turnbuckles, and all other flight control cables and turnbuckles at keel subframe 15A; and various follow-on actions, if necessary. This amendment is prompted by reports of chafing due to insufficient clearance between the flaps turnbuckle and the subframe, and between the airbrakes cable and the subframe. The actions specified by this AD are intended to prevent such chafing, which could result in damage to the flaps turnbuckle and the airbrakes cable, and subsequent fraying or seizing of the flight control cables. These conditions, if not corrected, could result in restriction or loss of the flight controls.

Final rule.

96-11-17 BEECH AIRCRAFT CORPORATION (Formerly DeHavilland; Hawker Siddeley; British Aerospace, PLC; Raytheon Corporate Jets, Inc.): Amendment 39-9641. Docket 95-NM- 180-AD.

Applicability: Model BAe 125 series 1000A and Model Hawker 1000 airplanes, as listed in Hawker Service Bulletin SB.27-168, dated July 17, 1995; 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.

NOTE 2: Beech (Raytheon) Model BAe 125 series 800B and BAe 125 series 1000B airplanes are similar in design to the airplanes that are subject to the requirements of this AD and, therefore, also may be subject to the unsafe condition addressed by this AD. However, as of the effective date of this AD, those models are not type certificated for operation in the United States. Airworthiness authorities of countries in which the Model BAe 125 series 800B and BAe 125 series 1000B airplanes are approved for operation should consider adopting corrective action, applicable to those models, that is similar to the corrective action required by this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent restriction or loss of the flight controls due to insufficient clearance and resultant chafing and damage to the flaps cable and/or turnbuckle and the airbrakes cable, accomplish the following:

(a) Within 6 months after the effective date of this AD: Perform a one-time detailed visual inspection for adequate working clearances and for damage of the flap, airbrakes, and other flight control cables and turnbuckles with the structure at keel subframe 15A (left- and right-hand sides) specified in Hawker Service Bulletin SB.27-168, dated July 17, 1995. Perform the inspection in accordance with that service bulletin. The detailed visual inspection for working clearances shall be conducted for each affected flight control through its full range of travel.

(1) If all clearances are within the limits specified in the service bulletin, and no damage is found: No further action is required by this AD.

(2) If the clearance for the flaps controls is outside the limits specified in the service bulletin: Prior to further flight, accomplish Modification SB 27-168-253705B in accordance with the service bulletin.

(3) If the clearance for the airbrakes controls is outside the limits specified in the service bulletin: Prior to further flight, repair in accordance with the service bulletin.

(4) If any cable is found to be damaged, and the damage exceeds the limits defined in Chapter 20-10-31 of the Airplane Maintenance Manual: Prior to further flight, replace the damaged cable with a new cable in accordance with the service bulletin.

(5) If any turnbuckle, keel subframe, or polythene strip is found to be damaged: Prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(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. 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 3: 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) The actions shall be done in accordance with Hawker Service Bulletin SB.27-168, dated July 17, 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 Raytheon Aircraft Company, 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 atthe Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(e) This amendment becomes effective on July 9, 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 certain Beech (Raytheon) Model BAe 125 series 1000A and Model Hawker 1000 airplanes was published in the Federal Register on March 12, 1996 (61 FR 9959). That action proposed to require a one-time visual inspection for adequate clearances between, and/or damage to, the flap cables and turnbuckles, airbrakes cables and turnbuckles, and all other flight control cables and turnbuckles at keel subframe 15A (left- and right-hand side); and various follow-on actions, if necessary.

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.

Changes to the Final Rule
The FAA has revised the final rule to correctly designate the affected airplane models as "Beech(Raytheon) Model BAe 125 series 1000A and Model Hawker 1000 airplanes."

Additionally, a new "NOTE 2" has been added to the final rule to clarify that airworthiness authorities of countries in which Beech (Raytheon) Model BAe 125 series 800B and BAe 125 series 1000B airplanes are approved for operation should consider adopting corrective action that is similar to that required by this AD, since those airplanes are similar in design to the affected airplanes.

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 with the changes previously described. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

Cost Impact
The FAA estimates that 25 airplanes of U.S. registry will be affected by this AD, that it will 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 $1,500, 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.

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 USC 106(g), 40113, 44701.

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