[Federal Register Volume 63, Number 130 (Wednesday, July 8, 1998)]
[Proposed Rules]
[Pages 36864-36866]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-18008]


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 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 63, No. 130 / Wednesday, July 8, 1998 / 
Proposed Rules  

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-23-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Models 1900, 
1900C, and 1900D Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to supersede Airworthiness Directive 
(AD) 97-14-16, which currently 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, repairing or replacing any part showing wear, and 
replacing any bracket with elongated holes on Raytheon Aircraft Company 
(Raytheon) Models 1900, 1900C, and 1900D airplanes. The proposed AD 
would retain the actions required in AD 97-14-16, and would increase 
the number of repetitive inspections by reducing the number of ground-
air-ground (GAG) cycles allowed between inspections. The proposed AD 
would also lower the total GAG cycles accumulated before the required 
initial inspection. The actions specified by the proposed AD are 
intended to prevent asymmetric flaps, jammed flaps, and/or possible 
interference between the flap and the aileron, which could inhibit 
aileron travel and result in possible loss of roll control of the 
airplane.

DATES: Comments must be received on or before September 18, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 98-CE-23-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106. Comments may be inspected at this location 
between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
    Service information that applies to the proposed AD may be obtained 
from Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085. This information also may be examined at the Rules Docket at the 
address above.

FOR FURTHER INFORMATION CONTACT: Mr. Steven E. Potter, Aerospace 
Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport 
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 
946-4124; facsimile: (316) 946-4407.

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 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, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    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 that summarizes 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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 98-CE-23-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, Central Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 98-CE-23-AD, Room 1558, 601 E. 12th Street, Kansas 
City, Missouri 64106.

Discussion

    AD 97-14-16, Amendment 39-10074, (62 FR 37128, July 11, 1997) 
currently 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, 
repairing or replacing any part showing wear, and replacing any bracket 
found with elongated holes on Raytheon Models 1900, 1900C, and 1900D 
airplanes.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 97-14-16, the manufacturer has reported to 
the FAA that another incident of flap roll bearings wearing on the flap 
attachment brackets has occurred on a Raytheon 1900 series airplane. 
This makes a total of five incidents of aileron interference on these 
airplanes. Because the most recent incident occurred at a much lower 
number of GAG cycles than the preceding incidents, the FAA believes the 
number of flights accumulated before the initial and repetitive 
inspections required in AD 97-14-16 should be reduced.

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 
procedures for repairing or replacing the part. The new service 
information issued, Raytheon Aircraft Mandatory Service Bulletin No. SB 
27-3158, Issued: June, 1998, is basically the same action as the 
information referenced above, except for a change in the initial and 
repetitive compliance times.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, the FAA has 
determined that AD action should be taken to preclude interference 
between the flap and the aileron, which could help prevent aileron 
travel.

[[Page 36865]]

    This condition, if not corrected, could result in loss of 
directional control of the airplane during critical phases of flight.

Explanation of the Provisions of the Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Raytheon Models 1900, 1900C, and 1900D 
airplanes of the same type design, the proposed AD would supersede AD 
97-14-16 with a new AD. The proposed AD would require the same actions 
required in AD 97-14-16, which are:

--Repetitively inspecting the outboard flap attachment brackets and aft 
roller bearings for wear;
--Inspecting for elongation of the holes in the flap attachment 
brackets;
--Repairing or replacing any part showing wear; and
--Replacing any bracket found with elongated holes.

    In addition, the proposed AD would change the compliance time by 
reducing the required number of GAG cycles accumulated prior to the 
initial inspection and the number of GAG cycles required between the 
repetitive inspections.

Differences Between the Service Bulletin and the Proposed AD

    The Raytheon Aircraft Mandatory Service Bulletin No. SB 27-3158, 
Issued: June, 1998, specifies that the initial inspection be 
accomplished at the accumulation of 1,200 GAG cycles, with the 
repetitive inspections occurring every 1,200 GAG cycles. The FAA is 
proposing that the GAG cycles be reduced to 600 for the initial 
inspections and 600 GAG cycles between the repetitive inspections. The 
FAA is using GAG cycles while the Raytheon service information is using 
flap cycles, which varies by a factor of two.
    The FAA's reason for reducing the GAG cycles by half is that the 
unsafe condition could occur during critical phases of flight. The FAA 
must also consider that an unsafe condition on commuter aircraft 
warrants additional caution.

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 occur over time. 
Examination of the most recent referenced incident and all information 
available to the FAA indicates that this problem has the potential of 
becoming detectable at around 1,200 flap cycles. To ensure that this 
unsafe condition does not occur during flight, the FAA is using 2 flap 
cycles per ground-air-ground cycle; therefore the proposed initial 
inspection would be required at a total accumulation of 600 GAG cycles. 
The repetitive inspection would be required every 600 GAG cycles.
    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 
Raytheon 1900 series airplanes would reach the above thresholds between 
42 days to 75 days from the initial service date of the airplane, and 
every 42 to 75 days after each repetitive inspection.
    For these reasons, the FAA has determined that the inspections 
required by the proposed AD should occur ``Upon the accumulation of 600 
total GAG cycles, or within the next 100 GAG cycles after the effective 
date of this AD, whichever occurs later, or within 600 GAG cycles from 
the date of the last inspection required by AD 97-14-16, unless already 
accomplished, and thereafter at intervals not to exceed 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 
600 GAG cycle time, so as not to inadvertently ground the affected 
airplanes.

Cost Impact

    The FAA estimates that 527 airplanes in the U.S. registry would be 
affected by the proposed AD, that it would take approximately 2 
workhours per airplane to accomplish the proposed inspection, that it 
would take approximately 8 workhours to accomplish the proposed repair, 
and that the average labor rate is approximately $60 an hour. Parts 
cost approximately $440 per airplane. Based on these figures, the total 
cost impact of the proposed AD on U.S. operators is estimated to be 
$63,240, or $120 per airplane
    These figures are calculated on the basis that the proposed 
inspection would be the only cost required. The proposed repair would 
be on the condition that damage would be found as a result of the 
inspection.
    The cost impact to the owner/operators of the affected airplanes 
could possibly double since the FAA is proposing a reduction of the 
number of required GAG cycles between the proposed inspections. The FAA 
is not able to determine the number of repetitive inspections that 
would occur over the life of the airplane.

Regulatory Impact

    The regulations proposed herein would 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 
proposal would 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) 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 has been placed 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 14 
CFR part 39 of the Federal Aviation Regulations 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 removing Airworthiness Directive 
(AD) 97-14-16, Amendment 39-10074 (62 FR 37128, July 11, 1997), and by 
adding a new AD to read as follows:

Raytheon Aircraft Company (Type Certificate No. A24CE formerly held 
by the Beech Aircraft Corporation): Docket No. 98-CE-23-AD; 
Supersedes AD 97-14-16, Amendment 39-10074.
    Applicability: The following model and serial number airplanes, 
certificated in any category:

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                 Model                             Serial Nos.          
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1900..................................  UA-1 and UA-3.                  

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1900C.................................  UB-1 through UB-74, and UC-1    
                                         through UC-174.                
1900C (C-12J).........................  UD-1 through UD-6.              
1900D.................................  UE-1 through all serial numbers.
------------------------------------------------------------------------

    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 in the body of this AD, unless 
already accomplished.

    Note 2: The compliance time of this AD takes precedence over the 
compliance time set out in the Raytheon Aircraft Mandatory Service 
Bulletin No. SB 27-3158, Issued: June, 1998.
    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 multiplying each hour TIS by 2, to calculate the 
number of GAG cycles. For example, 1,300 hours TIS would equal 2,600 
GAG cycles.
    To prevent asymmetric flaps, jammed flaps, and/or possible 
interference between the flap and the aileron, which could inhibit 
aileron travel and result in possible loss of roll control of the 
airplane, accomplish the following:
    (a) Upon the accumulation of 600 total ground-air-ground (GAG) 
cycles, or within 600 GAG cycles from the date of the last 
inspection required by AD 97-14-16, or within the next 100 GAG 
cycles after the effective date of this AD, whichever occurs later, 
and thereafter at intervals not to exceed 600 GAG cycles, 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 17 in Raytheon Aircraft 
(Raytheon) Mandatory Service Bulletin No. SB 27-3158, Issued: June, 
1998.
    (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 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 (ACO), Room 100, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209.
    (1) The request shall be forwarded through an appropriate FAA 
Maintenance Inspector, who may add comments and then send it to the 
Manager. Wichita ACO.
    (2) Alternative methods of compliance approved for AD 97-14-16 
are not considered approved as alternative methods of compliance for 
this AD.

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

    (e) All persons affected by this directive may obtain copies of 
the document referred to herein upon request to Raytheon Aircraft 
Company, 9709 E. Central, P. O. Box 85, Wichita, Kansas 67201-0085; 
or may examine this document at the FAA, Central Region, Office of 
the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, 
Missouri 64106.
    (f) This amendment supersedes AD 97-14-16, Amendment 39-10074.

    Issued in Kansas City, Missouri, on June 29, 1998.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-18008 Filed 7-7-98; 8:45 am]
BILLING CODE 4910-13-P