[Federal Register Volume 63, Number 48 (Thursday, March 12, 1998)]
[Rules and Regulations]
[Pages 11987-11989]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6327]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-68-AD; Amendment 39-10389; AD 98-05-03]
RIN 2120-AA64


Airworthiness Directives; de Havilland Model DHC-8-102 and -103 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting airworthiness directive (AD) 98-05-03 that was sent previously 
by individual notices to all known U.S. owners and operators of certain 
de Havilland Model DHC-8-102 and -103 series airplanes. This AD 
requires a one-time inspection to detect disbonding of the upper and 
lower skin panels of the horizontal stabilizer, and repair, if 
necessary. This action 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 reduced 
strength capability and consequent failure of the horizontal 
stabilizer, which can result in loss of controllability of the 
airplane.

DATES: Effective March 17, 1998, to all persons except those persons to 
whom it was made immediately effective by emergency AD 98-05-03, issued 
February 25, 1998, which contained the requirements of this amendment.
    Comments for inclusion in the Rules Docket must be received on or 
before April 13, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-68-AD, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056.
    The applicable service information may be obtained from Bombardier, 
Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, 
Montreal, Quebec H3C 3G9, Canada. This information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Serge Napoleon, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7512; 
fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: On February 25, 1998, the FAA issued 
emergency AD 98-05-03, which is applicable to certain de Havilland 
Model DHC-8-102 and -103 series airplanes.
    Transport Canada Aviation (TCA), which is the airworthiness 
authority for Canada, recently notified the FAA that an unsafe 
condition may exist on certain de Havilland Model DHC-8-102 and -103 
series airplanes. TCA advises that it has received reports of 
disbonding of the doublers and stringers from the upper and lower skin 
panels of the horizontal stabilizer. The bonding process of the 
horizontal stabilizer may have been improperly carried out during 
production; this bonding process has been discontinued. Such 
disbonding, if not corrected, could result in reduced strength 
capability and consequent failure of the horizontal stabilizer, which 
can result in loss of controllability of the airplane.
    TCA issued Canadian airworthiness directive CF-98-01, dated 
February 19, 1998, in order to assure the continued airworthiness of 
these airplanes in Canada.

FAA's Conclusions

    This airplane model is manufactured in Canada 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, TCA has kept the FAA informed of the 
situation described above. The FAA has examined the findings of TCA, 
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 the Requirements of the Rule

    Since the unsafe condition described is likely to exist or develop 
on other airplanes of the same type design registered in the United 
States, the FAA issued emergency AD 98-05-03 to prevent reduced 
strength capability and consequent failure of the horizontal 
stabilizer, which can result in loss of controllability of the 
airplane. The AD requires a one-time inspection to detect disbonding of 
the upper and lower skin

[[Page 11988]]

panels of the horizontal stabilizer, and repair, if necessary.
    This AD also requires that operators report inspection results--
positive or negative--to the FAA.

Interim Action

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

Differences Between This Rule and the Foreign Airworthiness 
Directive

    Operators should note that, although the parallel Canadian 
airworthiness directive specifies that the manufacturer may be 
contacted for disposition of certain repair conditions, this rule 
requires the repair of those conditions to be accomplished in 
accordance with a method approved by the FAA.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual notices 
issued on February 25, 1998, to all known U.S. owners and operators of 
certain de Havilland Model DHC-8-102 and -103 series airplanes. These 
conditions still exist, and the AD is hereby published in the Federal 
Register as an amendment to section 39.13 of the Federal Aviation 
Regulations (14 CFR 39.13) to make it effective as to all persons.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 98-NM-68-AD.'' The postcard will be date stamped and 
returned to the commenter.

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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, 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.


Sec. 39.13  [Amended]

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

98-05-03  De Havilland Inc.: Amendment 39-10389. Docket 98-NM-68-AD.

    Applicability: Model DHC-8-102 and -103 series airplanes, serial 
numbers 003 through 050 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 (d) 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.
    To prevent reduced strength capability and consequent failure of 
the horizontal stabilizer, which can result in loss of 
controllability of the airplane, accomplish the following:

    Note 2: Accomplishment of the actions required by paragraph (a) 
of this AD is not intended to supersede the ongoing requirements of 
the Airworthiness Limitation identified in the Maintenance Review 
Board (MRB) report as Task 5500/01.

    (a) Perform a one-time ultrasonic bond inspection to detect 
disbonding of the upper and lower skin panels of the horizontal 
stabilizer, at the time specified in paragraph (a)(1) or (a)(2), as 
applicable, of this AD; in accordance with de Havilland Product 
Support Manual (PSM) 1-8-7A, part 5, section 55-00-01, dated July 
15, 1996.
    (1) For airplanes having serial numbers 010 through 040 
inclusive: Inspect within 20 flight cycles or 7 days after the 
effective date of this AD, whichever occurs first.
    (2) For airplanes having serial numbers 003 through 009 
inclusive and 041 through 050 inclusive: Inspect within 60 flight 
cycles or 7 days after the effective date of this AD, whichever 
occurs first.
    (b) If any disbonding is found during the inspection required by 
paragraph (a) of this AD: Prior to further flight, accomplish the 
actions specified by paragraph (b)(1), (b)(2), or (b)(3), as 
applicable, of this AD.
    (1) If the disbonding is below (smaller than) the limits 
specified in the PSM, no further action is required by this 
paragraph.
    (2) If the disbonding is within the limits specified in the PSM, 
repair the disbonded area in accordance with the DHC-8 Structural 
Repair Manual PSM 1-8-3.
    (3) If the disbonding exceeds the limits specified in the PSM or 
if a repair is not provided by the PSM, repair the disbonded area in 
accordance with a method approved by the Manager, New York Aircraft

[[Page 11989]]

Certification Office (ACO), FAA, Engine and Propeller Directorate.

    Note 3: Where differences between this AD and the parallel 
Canadian airworthiness directive exist, this AD prevails.

    (c) Within 2 days after performing the inspection required by 
paragraph (a) of this AD: Submit a report of inspection findings, 
regardless of the results, to the Manager, New York ACO, FAA, Engine 
and Propeller Directorate, 10 Fifth Street, Third Floor, Valley 
Stream, New York 11581; fax (516) 568-2716. The report must include 
the airplane serial number, the stringer number, and the extent 
(length or surface area) of disbonding. (Operators may follow the 
guidelines provided in Figure 2 of de Havilland PSM 1-8-7A for 
reporting requirements.) Information collection requirements 
contained in this regulation have been approved by the Office of 
Management and Budget (OMB) under the provisions of the Paperwork 
Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.
    (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, 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York ACO.

    (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.

    Note 5: The subject of this AD is addressed in Canadian 
airworthiness directive CF-98-01, dated February 19, 1998.

    (f) This amendment becomes effective on March 17, 1998, to all 
persons except those persons to whom it was made immediately 
effective by emergency AD 98-05-03, issued February 25, 1998, which 
contained the requirements of this amendment.

    Issued in Renton, Washington, on March 5, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-6327 Filed 3-11-98; 8:45 am]
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