02-29678. Airworthiness Directives; Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

This document proposes the adoption of a new airworthiness directive (AD) that is applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes. This proposal would require repetitive inspections for discrepancies of the internal fuselage skin panels located in the stub wing areas; and corrective action if necessary. This action is necessary to detect and correct heat damage to the fuselage skin panels caused by the leakage of hot air from one of the bleed air ducts inside the stub wing, which could result in reduced structural integrity of the engine support structure. This action is intended to address the identified unsafe condition.

DATES:

Comments must be received by December 23, 2002.

ADDRESSES:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2001-NM-334-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9 a.m. and 3 p.m., Monday through Friday, except Federal holidays. Comments may be submitted via fax to [phone]. Comments may also be sent via the Internet using the following address: [e-mail]. Comments sent via fax or the Internet must contain “Docket No. 2001-NM-334-AD” in the subject line and need not be submitted in triplicate. Comments sent via the Internet as attached electronic files must be formatted in Microsoft Word 97 for Windows or ASCII text.

The service information referenced in the proposed rule may be obtained from Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone [phone]; fax [phone].

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of the proposed rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this action may be changed in light of the comments received.

Submit comments using the following format:

• Organize comments issue-by-issue. For example, discuss a request to change the compliance time and a request to change the service bulletin reference as two separate issues.
• For each issue, state what specific change to the proposed AD is being requested.
• Include justification (e.g., reasons or data) for each request.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report summarizing each FAA-public contact concerned with the substance of this proposal will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this action must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket Number 2001-NM-334-AD.” The postcard will be date stamped and returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2001-NM-334-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

Discussion

The Civil Aviation Authority—The Netherlands (CAA-NL), which is the airworthiness authority for the Netherlands, notified the FAA that an unsafe condition may exist on all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes. The CAA-NL advises that it has received reports of heat damage to the internal fuselage skin panels located in the stub wing areas. The cause of the heat damage was the leakage of hot air from one of the bleed air ducts inside the stub wing. Evidence of the heat damage was yellow discoloration of the primer paint on the inside of the fuselage. This condition, if not corrected, could result in reduced structural integrity of the engine support structure.

Explanation of Relevant Service Information

Fokker Services B.V. has issued Service Bulletin F28/53-151, dated June 4, 2001. The service bulletin describes procedures for repetitive visual inspections of the internal fuselage skin panels in the stub wing areas to detect discoloration of the primer paint due to heat damage, buckling or waviness of the skin panel, loose or missing fasteners, or fasteners with sheared-off heads; and corrective actions if necessary. The corrective actions include an eddy current inspection; measurement of the length and depth of buckles or waves in the skin panel; repair or replacement of skin panels with heat damage, buckling, or waviness that are not within the acceptable limits specified in the service bulletin; and replacement of loose and/or missing fasteners, or fasteners having sheared-off heads, with new fasteners. The CAA-NL classified this service bulletin as mandatory and issued Dutch airworthiness directive 2001-093, dated July 31, 2001, in order to assure the continued airworthiness of these airplanes in the Netherlands.

FAA's Conclusions

This airplane model is manufactured in the Netherlands and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the CAA-NL has kept the FAA informed of the situation described above. The FAA has examined the findings of the CAA-NL, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, the proposed AD would require accomplishment of the actions specified in the service bulletin described previously.

Interim Action

This is considered to be an interim action until a final action is identified, at which time the FAA may consider further rulemaking.

Cost Impact

The FAA estimates that 24 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 1 work hour per airplane to accomplish the proposed inspection, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $1,440, or $60 per airplane, per inspection cycle.

The cost impact figure discussed above is based on the assumption that no operator has yet accomplished any of the proposed requirements of this AD action, and that no operator would accomplish those actions in the future if this proposed AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.

Regulatory Impact

The regulations proposed herein would 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 proposal would not have federalism implications under Executive Order 13132.

For the reasons discussed above, I certify that this proposed regulation (1) is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, 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 copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• Safety

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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:

Fokker Services B.V.: Docket 2001-NM-334-AD.

Applicability: All Model F.28 Mark 1000, 2000, 3000, and 4000 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 (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 detect and correct heat damage to the fuselage skin panels caused by the leakage of hot air from one of the bleed air ducts inside the stub wing, and consequent reduced structural integrity of the engine support structure; accomplish the following:

Repetitive Inspections

(a) Within 6,000 flight cycles after the effective date of this AD: Perform a general visual inspection of the internal fuselage structure between frames 16060 and 16660 and the beams at the upper and lower stub wing angles in the stub wing (engine pylon) areas, for discoloration of the primer paint, buckling or waviness of the skin panel, loose and/or missing fasteners, or fasteners with sheared-off heads, by accomplishing all actions specified in Part 1 of the Accomplishment Instructions of Fokker Service Bulletin F28/53-151, dated June 4, 2001. Repeat the inspection at intervals not to exceed 6,000 flight cycles.

Note 2:

For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”

Corrective Actions

(b) Except as provided by paragraph (c) of this AD, if any discrepancy is found (i.e., primer paint discoloration; buckling or waviness of the skin panel; missing, damaged, or loose rivets) during the general visual inspection required by paragraph (a) of this AD, before further flight, perform the applicable follow-on corrective actions (e.g., eddy current inspection; measurement of the length and depth of buckles or waves in the skin panel; repair of skin panels with heat damage, buckling, or waviness that are not within the acceptable limits specified in the service bulletin, or replacement with new skin panels; and replacement of loose and/or missing fasteners, or fasteners having sheared-off heads with new fasteners; as applicable) specified in the Accomplishment Instructions of Fokker Service Bulletin F28/53-151, dated June 4, 2001.

(c) If buckling or waviness of the skin panel is detected during the general visual inspection required by paragraph (a) of this AD, and the depth is within the limits specified in Part 2, paragraph C.(2) of the Accomplishment Instructions of Fokker Service Bulletin F28/53-151, dated June 4, 2001, the affected area must be repaired within 2,000 flight cycles after accomplishment of the inspection required by paragraph (a) of this AD.

(d) Repair or replacement of damaged fuselage skin panels or fasteners does not terminate the repetitive inspections required by 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, International Branch, ANM-116, Transport Airplane Directorate, FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.

Note 3:

Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

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.

Note 4:

The subject of this AD is addressed in Dutch airworthiness directive 2001-093, dated July 31, 2001.

Issued in Renton, Washington, on November 15, 2002.

Vi L. Lipski,

Manager, Transport Airplane Directorate, Aircraft Certification Service.