AD 2000-11-20

This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100 and -300 series airplanes, that requires revising the Aircraft Log Book to correct the airplane Production Modification List; performing an inspection to determine which bonded skin panels on the airplane require bonding integrity inspections (BII); and revising the Airworthiness Limitations List of the Approved Maintenance Plan to include the BII requirements. This amendment also requires, for certain airplanes, repetitive ultrasonic bond inspections to detect disbonding of airplane skin panels, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent damage to bonded skin panels to go undetected, which could result in failure of the bonded skin panels, and consequent loss of controllability of the airplane.

Final rule.

2000-11-20 BOMBARDIER INC. (Formerly de Havilland, Inc.): Amendment 39-11768. Docket 98-NM-380-AD.

Applicability: Model DHC-8-100 and -300 series airplanes, serial numbers 215 through 341 inclusive; 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 (e) 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 damage to bonded skin panels to go undetected, which could result in failure of the bonded skin panels, and consequent loss of controllability of the airplane, accomplish the following:

Revision to Aircraft Log Book and Airworthiness Limitations List

(a) Within 30 days after the effective date of this AD, perform the actions required by paragraphs (a)(1), (a)(2), and (a)(3) of this AD.

(1) Revise the Aircraft Log Book to correct the airplane Production Modification List in accordance with the Accomplishment Instructions in Part A of Section III of Bombardier Service Bulletin S.B. 8-51-2, Revision `A,' dated September 19, 1998.

(2) Perform an inspection to determine which bonded skin panels on the airplane require bonding integrity inspections (BII) in accordance with the Accomplishment Instructions in Part B of Section III of Bombardier Service Bulletin S.B. 8-51-2, Revision `A,' dated September 19,1998.

(3) Revise the Airworthiness Limitations List of the Approved Maintenance Plan by inserting the bonding integrity inspections identified as de Havilland Maintenance Task 5500/01 and de Havilland Maintenance Task 5700/01 into the Airworthiness Limitations List. Except as provided by paragraph (e) of this AD: After the actions specified in paragraph (a)(3) of this AD have been accomplished, no alternative replacement times or structural inspection intervals may be approved for the bonded panels of the empennage and wings specified in de Havilland Maintenance Task 5500/01 and de Havilland Maintenance Task 5700/01.

On-Condition Repetitive Inspections

(b) For airplanes on which the bonded skin panels require BII's, as determined in paragraph (a)(2) of this AD: At the next required maintenance visit, but no later than 12 months after the effective date of this AD, perform an initial ultrasonic bond inspection to detect disbonding of the skin panels, in accordance withPart 5, sections 55-00-01 and/or 57-30-01, of Bombardier Production Support Manual (PSM) 1-8-7A, dated December 15, 1998 (for Model DHC-8-100 series airplanes); or Part 5, sections 55-00-01 and 57-30-01 of Bombardier PSM 1-83-7A, dated April 30, 1999 (for Model DHC-8-300 series airplanes); as applicable. Thereafter, repeat the ultrasonic inspection at the interval specified in the applicable PSM.

On-Condition Repair

(c) Except as provided by paragraph (d) of this AD, if any disbonding is detected during any inspection required by paragraph (b) of this AD, prior to further flight, repair in accordance with Part 5, sections 55-00-01 and 57-30-01 of Bombardier PSM 1-8-7A, dated December 15, 1998 (for Model DHC-8-100 series airplanes); or Part 5, sections 55-00-01 and 57-30-01 of Bombardier PSM 1-83-7A, dated April 30, 1999 (for Model DHC-8-300 series airplanes); as applicable.

(d) If any disbonding is detected during any inspection required by paragraph (b) of this AD; andthe applicable service information specifies to contact Bombardier for appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. For a repair method to be approved by the Manager, New York ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD.

Alternative Methods of Compliance

(e) 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, New York ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO.

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

Special Flight Permits(f) 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.

Incorporation by Reference

(g) The Aircraft Log Book revision required by paragraph (a)(1) and the inspection required by paragraph (a)(2) of this AD shall be done in accordance with Bombardier Service Bulletin S.B. 8-51-2, Revision `A,' dated September 19, 1998. 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 Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office,10 Fifth Street, Third Floor, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

NOTE 3: The subject of this AD is addressed in Canadian airworthiness directive CF-98-31, dated September 1, 1998.

(h) This amendment becomes effective on July 18, 2000.

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 Bombardier Model DHC-8-100 and -300 series airplanes was published in the Federal Register on March 31, 2000 (65 FR 17206). That action proposed to require revising the Aircraft Log Book to correct the airplane Production Modification List; performing an inspection to determine which bonded skin panels on the airplane require bonding integrity inspections (BII); and revising the Airworthiness Limitations List of the Approved Maintenance Plan to include the BII requirements. That action also proposed to require, for certain airplanes, repetitive ultrasonic bond inspections to detect disbonding of airplane skin panels, and repair, if necessary.

Comments
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.

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

Cost Impact
The FAA estimates that 41 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 revisions to the Aircraft Log Book, Approved Maintenance Plan, and inspection, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the actions required by this AD on U.S. operators is estimated to be $2,460, 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 a substantial direct effect 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, it is determined that this final rule does not have federalism implications under Executive Order 13132.

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. 106(g), 40113, 44701.

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