AD 95-15-04

This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Corporate Jets Model BAe 125-800A and -1000A airplanes, that requires inspections to detect corrosion of the wing leading edge skins, including the wing anti-ice fluid distribution panel (TKS panel) rebate and radius; repair, if necessary; and subsequent corrosion protection treatment. This amendment also requires inspections and treatments of the landing/taxiing lamp window assembly recess and stall vane spoiler rebate/radius. This amendment is prompted by reports of corrosion of the wing leading edge skin at the interface with the TKS panels. The actions specified by this AD are intended to prevent reduced structural integrity of the wing leading edge section at the interface with the TKS panels and stall vane spoilers, which could adversely affect the flight characteristics of the airplane.

Final rule.

95-15-04 RAYTHEON CORPORATE JETS, INC. (Formerly DeHavilland, Inc.; Hawker Siddeley; British Aerospace, PLC): Amendment 39-9307. Docket 93-NM-105-AD.

Applicability: Model BAe 125-800A and -1000A airplanes, as listed in Raytheon Corporate Jets Service Bulletin S.B. 57-77, Revision 1, dated October 28, 1993, 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 use the authority provided in paragraph (c) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD.Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent reduced structural integrity of the wing leading edge skin and wing anti-ice fluid distribution panel (TKS panel) interface joint, which could adversely affect the flight characteristics of the airplane, accomplish the following:

(a) Accomplish the actions specified in paragraphs (a)(1), (a)(2), (a)(3), and (a)(4) of this AD within the time schedule indicated in each paragraph, and in accordance with Corporate Jets Limited Service Bulletin S.B. 57-77, dated May 20, 1993, or Raytheon Corporate Jets Service Bulletin S.B. 57-77, Revision 1, dated October 28, 1993.

(1) Within 24 months since airplane manufacture, or within 12 months after the effective date of this AD, whichever occurs later, perform a detailed visual inspection to detect corrosion of the polished surface of the top and bottom leading edge skins on each wing, in accordance with either service bulletin.

(i) If any corrosion is detected and that corrosion is within the limits specified in either service bulletin, prior to further flight, remove the corrosion in accordance with either service bulletin.

(ii) If any corrosion is detected and that corrosion exceeds the limits specified in either service bulletin, prior to further flight, repair the wing leading edge skins in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(2) Prior to further flight after accomplishing the actions required by paragraph (a)(1) of this AD, conduct a detailed visual inspection to detect corrosion of the wing anti-ice fluid distribution panel (TKS panel) rebate and radius, on the topand bottom leading edge skin section on each wing, in accordance with either service bulletin.

(i) If any corrosion is detected and that corrosion is within the limits specified in either service bulletin, prior to further flight, remove the corrosion in accordance with either service bulletin.

(ii) If any corrosion is detected and that corrosion exceeds the limits specified in either service bulletin, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(3) Prior to further flight after accomplishing the actions required by paragraph (a)(2) of this AD, conduct a dye penetrant inspection to detect corrosion of the TKS panel rebate and radius, on the top and bottom leading edge skin section on each wing, in accordance with either service bulletin.

(i) If any corrosion is detected and that corrosion is within the limits specified in either service bulletin, prior to further flight, remove the corrosion in accordance with either service bulletin.

(ii) If any corrosion is detected and that corrosion exceeds the limits specified in the service bulletin, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(4) Prior to further flight after accomplishing the actions required by paragraph (a)(3) of this AD, accomplish both of the following actions in accordance with either service bulletin:

(i) Apply enhanced protective treatment to the TKS panel rebate and radius, on the top and bottom leading edge skin section on each wing; and

(ii) Conduct a flight check of the airplane stall warning system and stall characteristics.

(b) Accomplish the actions specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD within the time schedule indicated in each paragraph, and in accordance with Raytheon Corporate Jets Service Bulletin S.B. 57-77, Revision 1, dated October 28, 1993:

NOTE 2: Any inspection specified in paragraph (b)(1), (b)(2), and (b)(3) of this AD that was conducted prior to the effective date of this AD in accordance with Corporate Jets Limited Service Bulletin S.B. 57-77, dated May 20, 1993, is considered to be in compliance with this paragraph.

NOTE 3: The actions required by paragraph (b) of this AD may be accomplished in conjunction with the actions required by paragraph (a) within the compliance time required by paragraph (a).

(1) Within 2 years after the effective date of this AD, conduct a detailed visual inspection to detect corrosion of the landing/taxiing lamp window assembly recess and the stall vane spoiler rebate and radius, on the top and bottom leading edge skin section on each wing, in accordance with the service bulletin.

(i) If any corrosion is detected and that corrosion is within the limits specified in either service bulletin, prior to further flight, remove the corrosion in accordance with the service bulletin.

(ii) If any corrosion is detected and that corrosion exceeds the limits specified in either service bulletin, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(2) Prior to further flight after accomplishing the actions required by paragraph (b)(1) of this AD, conduct a dye penetrant inspection to detect corrosion of the landing/taxiing lamp window assembly recess and the stall vane spoiler rebate and radius, on the top and bottom leading edge skin section on each wing, in accordance with the service bulletin.

(i) If any corrosion is detected and that corrosion is within the limits specified in either service bulletin, prior to further flight, remove the corrosion in accordance with the service bulletin.

(ii) If any corrosion is detected and that corrosion exceeds the limits specified ineither service bulletin, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(3) Prior to further flight after accomplishing the actions required by paragraph (b)(2) of this AD, accomplish both of the following actions in accordance with the service bulletin:

(i) Apply enhanced protective treatment to the landing/taxiing lamp window assembly recess and the stall vane spoiler rebate and radius, on the top and bottom leading edge skin section on each wing; and

(ii) Conduct a flight check of the airplane stall warning system and stall characteristics.

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

(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.

(e) The actions shall be done in accordance with the following service bulletins, as applicable, which contain the specified effective pages:

Service Bulletin
Referenced and Date

Page Number
Revision Level Shown on Page
Date
Shown on Page
Corporate Jets Limited
S.B. 57-77,
May 20, 1993
1-13
Original
May 20, 1993
Raytheon Corporate Jets
S.B. 57-77,
Revision 1,
October 28, 1993
1-9, A1-A5

10-14
1

Original
October 28, 1993

May20, 1993

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 Corporate Jets, Inc., 3 Bishops Square Street, Albans Road West, Hatfield, Hertfordshire, AL109NE, United Kingdom. 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.

(f) This amendment becomes effective on August 23, 1995.

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 Raytheon Corporate Jets Model BAe 125-800A and -1000A airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on April 17, 1995 (60 FR 19183). That action proposed to require inspections to detect corrosion of the wing leading edge skins, including the wing anti-ice fluid distribution panel (TKS panel) rebate and radius; repair, if necessary; and subsequent corrosion protection treatment. That action also proposed to require inspections and treatments of the landing/taxiing lamp window assembly recess and the stall vane spoiler rebate/radius.

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. TheFAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that 154 Model BAe 125-800A and -1000A airplanes of U.S. registry will be affected by this AD. It will take approximately 130 work hours per airplane to accomplish the inspections and treatment of the wing leading edge skins (including the TKS rebate and radius) at an average labor rate of $60 per work hour. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $1,201,200, or $7,800 per airplane.

The total 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 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89.

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