AD Amdt-39-10074

[Federal Register Volume 62, Number 133 (Friday, July 11, 1997)]
[Rules and Regulations]
[Pages 37128-37130]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 97-18064]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-47-AD; Amendment 39-10074; AD 97-14-16]
RIN 2120-AA64


Airworthiness Directives: Raytheon Aircraft Company (Formerly 
Beech Aircraft Corporation) Model 1900 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to all Raytheon Aircraft Company (Raytheon) 1900 series 
airplanes. This action requires repetitively inspecting the flap aft 
roller bearings and flap attachment brackets for indications of contact 
(wear), inspecting for elongation of the holes in the flap attachment 
brackets, and repairing or replacing any part showing wear. The actions 
specified by this AD

[[Page 37129]]

are intended to prevent interference between the flap and the aileron 
which could inhibit aileron movement and result in possible loss of 
control of the airplane.

DATES: Effective August 4, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 4, 1997.
    Comments for inclusion in the Rules Docket must be received on or 
before September 4, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket 97-CE-47-AD, Room 1558, 601 E. 12th 
Street, Kansas City, Missouri 64106.
    Service information that applies to this AD may be obtained from 
Raytheon Aircraft Company, 9709 E. Central, P. O. Box 85, Wichita, 
Kansas 67201-0085. This information may also be examined at the Federal 
Aviation Administration (FAA), Central Region, Office of the Assistant 
Chief Counsel, Attention: Rules Docket 97-CE-47-AD, Room 1558, 601 E. 
12th Street, Kansas City, Missouri 64106; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Mr. Steve Potter, Aerospace Engineer, 
Wichita Aircraft Certification Office, Room 100, 1801 Airport Road, 
Mid-Continent Airport, Wichita, Kansas 67209, telephone (316) 946-4128; 
facsimile (316) 946-4164.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA has received three reports of Raytheon Aircraft Company 
(Raytheon) 1900 series airplanes entering into an uncommanded roll 
after setting the flaps at 35 deg.. In each incident, the operator 
applied extreme force to the control wheel to counter the roll and 
landed.
    Further investigation revealed that the outboard flaps detached 
from the flap aft roller bearings at the outboard flap inboard flap 
track. Detachment of the outboard flap from the roller bearing results 
in a flap asymmetric condition causing contact between the outboard 
flap and the aileron, consequently inhibiting aileron movement. In 
addition, as the flap aft roller bearing detaches from the outboard 
flap, the outer flange element of the roller bearing repositions on the 
bearing, resulting in contact between the outer flange element and the 
attachment bracket. This contact eventually wears through the 
attachment bracket allowing the outboard flap to detach from the aft 
roller bearing.

Relevant Service Information

    Raytheon has issued Safety Communique No. 137, dated May, 1997, 
which specifies procedures for inspecting the flap attachment brackets 
for signs of wear, and inspecting the aft roller bearing attachment 
holes for elongation. If wear from contact is visible or the roller 
bearing attachment holes are elongated, the Safety Communique specifies 
repairing or replacing the part.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, including the 
relevant service information, the FAA has determined that AD action 
should be taken to preclude interference between the flap and the 
aileron, which could prevent aileron movement and result in possible 
loss of control of the airplane.

Explanation of the Provisions of the AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Raytheon 1900 series airplanes of the same 
type design, this AD requires repetitively inspecting the outboard flap 
attachment brackets and aft roller bearings for wear, inspecting for 
elongation of the holes in the flap attachment brackets, and repairing 
or replacing any part showing wear. The actions are to be done in 
accordance with the instructions in Raytheon Aircraft Safety Communique 
No. 137, dated May, 1997 and Temporary Revision No. 57-1 to Raytheon 
Aircraft Company Beech 1900 Airliner Series Structural Repair Manual, 
part number 114-590021-9B, dated May 16, 1997; Reissued June 30, 1992.

Justification of Compliance Time and Determination of the Effective 
Date of This AD

    Wear of the flap aft roller bearings and flap attachment brackets 
and elongation of the flap attachment bracket holes occurs over time. 
Examination of the referenced incidents and all information available 
to the FAA indicates that this problem has the potential of becoming 
detectable at around 2,600 ground-air-ground (GAG) cycles. Numerous 
1900 series airplanes are either currently over or closely approaching 
this 2,600 GAG cycle threshold. These airplanes are utilized primarily 
in commuter service. Operators of these airplanes average anywhere from 
8 GAG cycles per day to 14 GAG cycles per day. Based on these averages, 
operators of 1900 series airplanes would reach the above thresholds 
between 185 days to 325 days after manufacture of the airplane, and 
thereafter every 185 to 325 days after each inspection.
    For these reasons, the FAA has determined that the inspections 
required by this AD should occur ``Upon the accumulation of 2,600 GAG 
cycles or within the next 100 GAG cycles after the effective date of 
this AD, whichever occurs later, unless already accomplished, and 
thereafter at intervals not to exceed 2,600 GAG cycles.'' The 100 GAG 
cycles for the initial compliance time is utilized to allow a grace 
period for those airplanes already over the 2,600 GAG cycle time, so as 
not to inadvertently ground the affected airplanes.

Determination of the Effective Date of the AD

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting immediate flight safety and, thus, was not 
preceded by notice and opportunity to 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 should 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 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

[[Page 37130]]

submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 97-CE-47-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 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 (otherwise, an evaluation is 
not required). A copy of it, if filed, may be obtained from the Rules 
Docket.

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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
(AD) to read as follows:

97-14-16. Raytheon Aircraft Company: Amendment 39-10074; Docket No. 
97-CE-47-AD.

    Applicability: Model 1900, 1900C, and 1900D airplanes (all 
serial numbers), 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 upon the accumulation of 2,600 ground-air-
ground (GAG) cycles or within the next 100 GAG cycles after the 
effective date of this AD, whichever occurs later, unless already 
accomplished within the last 2,500 GAG cycles, and thereafter at 
intervals not to exceed 2,600 GAG cycles.

    Note 2: The compliance time of this AD takes precedence over the 
compliance time set out in the Raytheon Safety Communique No. 137, 
dated May, 1997.
    Note 3: If the owners/operators of the affected airplane have 
not kept track of GAG cycles, hours time-in-service (TIS) may be 
substituted by calculating 2 GAG cycles per hour TIS. For example, 
2,600 GAG cycles would equal 1,300 hours TIS.

    To prevent interference between the flap and the aileron, which 
could inhibit aileron movement and result in possible loss of 
control of the airplane, accomplish the following:
    (a) Inspect the outboard flap attachment brackets and aft roller 
bearings on both wings for visible wear and elongation of the 
bracket holes in accordance with instructions 1 through 18 in 
Raytheon Aircraft (Raytheon) Safety Communique No. 137, dated May 
1997.
    (b) Prior to further flight, repair or replace any worn or 
damaged part in accordance with Temporary Revision No. 57-1 to the 
Raytheon Aircraft Beech 1900 Airliner Series Structural Repair 
Manual P/N 114-590021-9B, dated May 16,1997; Reissued June 30, 1992.
    (c) 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.
    (d) An alternative method of compliance or adjustment of the 
initial or repetitive compliance times that provides an equivalent 
level of safety may be approved by the Manager, Wichita Aircraft 
Certification Office, Room 100, 1801 Airport Road, Mid-Continent 
Airport, Wichita, Kansas 67209. The request shall be forwarded 
through an appropriate FAA Maintenance Inspector, who may add 
comments and then send it to the Manager, Wichita Aircraft 
Certification Office.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita Aircraft Certification Office.

    (e) The inspections and repairs required by this AD shall be 
done in accordance with Raytheon Aircraft Safety Communique No. 137, 
dated May, 1997 and Temporary Revision No. 57-1 to the Raytheon 
Aircraft Beech 1900 Airliner Series Structural Repair Manual P/N 
114-590021-9B, dated May 16,1997; Reissued June 30, 1992. 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 Aircraft Company, 9709 E. 
Central, P. O. Box 85, Wichita, Kansas 67201-0085. Copies may be 
inspected at the FAA, Central Region, Office of the Assistant Chief 
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.
    (f) This amendment (39-10074) becomes effective on August 4, 
1997.

    Issued in Kansas City, Missouri, on July 3, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-18064 Filed 7-10-97; 8:45 am]
BILLING CODE 4910-13-U