AD 95-19-13

This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146-100A, -200A, and -300A airplanes, that requires repetitive inspections for cracking of fuselage frame 29, and repair, if necessary. This amendment is prompted by testing that revealed fatigue cracking in the web and inboard flange of frame 29. The actions specified by this AD are intended to prevent reduced structural integrity of the fuselage due to fatigue cracking in frame 29.

Final rule

95-19-13 BRITISH AEROSPACE REGIONAL AIRCRAFT LIMITED, AVRO INTERNATIONAL AEROSPACE DIVISION (Formerly British Aerospace, plc; British Aerospace Commercial Aircraft, Limited): Amendment 39-9375. Docket 94-NM-131-AD.
Applicability: All Model BAe 146-100A, -200A, and -300A 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 use the authority provided in paragraph (d) 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 fuselage of the airplane due to fatigue cracking in frame 29, accomplish the following:

(a) Perform a detailed visual inspection for cracking of frame 29 between stringers 12 and 18 on the left and right side of the fuselage, in accordance with Avro International Aerospace Inspection Service Bulletin S.B. 53-130, dated May 10, 1994. If the polymer coating on frame 29 prevents a detailed visual inspection, perform a surface eddy current inspection for cracking in accordance with the service bulletin. Perform the inspections at the time specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable.

(1) For Model BAe 146-100A airplanes: Perform the inspection within 6 months after the effective date of this AD, or prior to the accumulation of 30,000 total landings, whichever occurs later. Repeat the inspection thereafter at intervals not to exceed 6,000 landings.

(2) For Model BAe 146-200A airplanes, and for Model BAe 146-300A airplanes other than those airplanes identified in paragraph (a)(3) of this AD: Perform the inspection within 6 months after the effective date of this AD, or prior to the accumulation of 24,000 total landings, whichever occurs later. Repeat the inspection thereafter at intervals not to exceed 6,000 landings.

(3) For Model BAe 146-300A airplanes having serial numbers E3207, E3212, E3214, E3216, E3218, E3219, and E3222: Perform the inspection within 6 months after the effective date of this AD, or prior to the accumulation of 13,000 total landings, whichever occurs later. Repeat the inspection thereafter at intervals not to exceed 4,000 landings.(b) If any cracking is found during any inspection required by paragraph (a) of this AD, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(c) Accomplishment of the modification of each affected bolt position in accordance with Avro International Aerospace Inspection Service Bulletin S.B. 53-130, dated May 10, 1994, prior to the embodiment times shown in Table 'A' of that service bulletin, constitutes terminating action for the repetitive inspections required by paragraph (a) of this AD.

NOTE 2: Repair Instruction Leaflet (RIL) HC536H9159 provides detailed instructions for modification of all bolt positions in the affected areas of frame 29.

(d) 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.

(e) 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.

(f) The inspections and modification shall be done in accordance with Avro International Aerospace Inspection Service Bulletin S.B. 53-130, dated May 10, 1994. 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 Avro International Aerospace, Inc., 22111 Pacific Blvd., Sterling, Virginia 20166. 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.

(g) This amendment becomes effective on October 20, 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 all British Aerospace Model BAe 146-100A, -200A, and -300A airplanes was published in the Federal Register on April 20, 1995 (60 FR 19693). That action proposed to require repetitive visual inspections to detect cracking of the fuselage at frame 29, and repair, if necessary.

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received.

The commenter supports the proposed rule.

After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that 43 airplanes of U.S. registry will be affected by this AD, that it will take approximately 9 work hours perairplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $23,220, or $540 per airplane, per inspection cycle.

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 USC 106(g), 40101, 40113, 44701.

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