[Federal Register Volume 64, Number 88 (Friday, May 7, 1999)]
[Rules and Regulations]
[Pages 24507-24510]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-11320]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-17-AD; Amendment 39-11160; AD 99-10-06]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Corporation Model 
Beech 2000 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 certain Raytheon Aircraft Corporation (Raytheon) Model Beech 
2000 airplanes. This AD requires immediately incorporating temporary 
revisions to the Limitations Section of the Airplane Flight Manual 
(AFM) that include requirements of not allowing flap operation during 
takeoff, accomplishing the preflight visual checks (referred to as 
visual inspections in the AFM temporary revisions) of the aft cove 
panel of the wing for delamination prior to each flight, and 
incorporating a repair scheme if delamination is found. This AD also 
requires repetitively inspecting the trailing edge of the wing by 
looking for

[[Page 24508]]

delamination (debonding) (also referred to as cracks in the service 
information) through the thickness of the trailing edge of the wing 
cove skin panels, and modifying the center flap track rib attachment 
when delamination (debonding) is found. This AD is the result of a 
report of the wing cove skin panel separating from the wing while in 
flight on one of the affected airplanes. The actions specified by this 
AD are intended to detect and correct delamination of the wing cove 
skin in the area of the support rib, which could result in the 
delamination propagating to the trailing edge of the wing with the wing 
cove skin panel possibly separating from the wing.

DATES: Effective June 3, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 3, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before July 9, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 99-CE-17-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.
    Service information that applies to this AD may be obtained from 
the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; 
telephone: (800) 429-5372 or (316) 676-3140. This information may also 
be examined at the Federal Aviation Administration (FAA), Central 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 99-
CE-17-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 E. Potter, Aerospace 
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 
946-4124; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA has received a report that the wing cove skin panel 
separated from the wing while in flight on a Raytheon Model Beech 2000 
airplane. Examination of this incident revealed delamination of the aft 
cove wing skin panel in the area of the support ribs, which then 
propagated to the wing aft cove panel until it separated.
    Raytheon has reported to the FAA other wing skin delaminations in 
this area on the affected airplanes.

Relevant Service Information

    Raytheon has issued the following:
    --Safety Communique No. 158, dated March 1999, which includes 
procedures for inspecting the trailing edge of the wing by looking for 
delamination (debonding) through the thickness of the trailing edge of 
the wing cove skin panels;
    --Raytheon Temporary Changes to the FAA Approved Airplane Flight 
Manual (AFM), part number (P/N) 122-590013-37BTC3, Rev. 1, dated March 
12, 1999, which include requirements of not allowing flap operation 
during takeoff, and accomplishing preflight visual checks (referred to 
as visual inspections in the AFM temporary revisions) of the aft cove 
panel of the wing for delamination prior to each flight and 
incorporating a repair scheme if delamination is found;
    --Field Repair drawing FR-SS-00010, Reinforcement of Aft cove panel 
of Flap Cove Assy P/N 122-100079-1/2, which includes procedures for 
modifying the aft cove panel of the flap cove assembly when 
delamination (debonding) is found; and
    --Kit 122-4019, Rev. B, dated March 12, 1999, which includes the 
procedures and parts necessary for modifying the attachment of the 
support rib at the center flap track when delamination (debonding) 
(referred to as cracks in the Safety Communique) is found.

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 detect and correct delamination of the wing cove 
skin in the area of the support rib, which could result in the 
delamination propagating to the trailing edge of the wing with the wing 
cove skin panel possibly separating from the wing.

Explanation of the Provisions of the AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Raytheon Model Beech 2000 airplanes of the 
same type design, the FAA is taking AD action. This AD requires 
immediately incorporating temporary revisions to the Limitations 
Section of the Airplane Flight Manual (AFM) that disallow flap 
operation during takeoff, and specify inspecting the aft cove panel of 
the wing for delamination prior to each flight and incorporating a 
repair scheme if delamination is found. This AD also requires 
repetitively inspecting the trailing edge of the wing by looking for 
delamination (debonding) (referred to as cracks in the service 
information) through the thickness of the trailing edge of the wing 
cove skin panels, and modifying the center flap track rib attachment 
when delamination (debonding) is found.
    Accomplishment of the actions specified in this AD is required in 
accordance with the service information previously referenced.

Determination of the Effective Date of the AD

    Since a situation exists (the wing cove skin panel possibly 
separating from the wing) that requires the immediate adoption of this 
regulation, it is found that notice and opportunity for public prior 
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 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to

[[Page 24509]]

Docket No. 99-CE-17-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:

99-10-06 Raytheon Aircraft Company: Amendment 39-11160; Docket No. 
99-CE-17-AD.

    Applicability: Model Beech 2000 airplanes, serial numbers NC-4 
through NC-53, certificated in any category, that do not have 
Raytheon Kit 122-4019, Rev. B, dated March 12, 1999, incorporated.

    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 (g) 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.
    To detect and correct delamination of the wing cove skin in the 
area of the support rib, which could result in the delamination 
propagating to the trailing edge of the wing with the wing cove skin 
panel possibly separating from the wing, accomplish the following:
    (a) Prior to further flight, incorporate Raytheon Temporary 
Changes to the FAA Approved Airplane Flight Manual (AFM), part 
number (P/N) 122-590013-37BTC3, Rev. 1, dated March 12, 1999, into 
the Limitations Section of the AFM. The requirements of the AFM 
temporary revisions include not allowing flap operation during 
takeoff and accomplishing preflight visual checks (referred to as 
visual inspections in the AFM temporary revisions) of the aft cove 
panel of the wing for delamination (debonding) prior to each flight 
and incorporating a repair scheme if delamination (debonding) is 
found.

    Note 2: The visual checks referenced in the AFM temporary 
revisions may be performed by the pilot.
    (b) Visually inspect the trailing edge of the wing by looking 
for delaminations (debonding) (also referred to as cracks in the 
service information) through the thickness of the trailing edge of 
the wing cove skin panel, in accordance with Raytheon Safety 
Communique No. 158, dated March 1999, at the compliance times 
specified in paragraphs (b)(1) and (b)(2) of this AD.
    (1) Initial Inspection: Within the next 10 hours time-in-service 
(TIS) after the effective date of this AD or prior to further flight 
after any delamination (debonding) is found during any preflight 
visual check specified in the AFM temporary revisions required by 
paragraph (a) of this AD, whichever occurs first; and
    (2) Repetitive Inspections: Thereafter (after each inspection) 
at intervals not to exceed 50 hours TIS or prior to further flight 
after any delamination (debonding) is found during any preflight 
check specified in the AFM temporary revisions required in paragraph 
(a) of this AD, whichever occurs first.
    (c) If any delamination (debonding) is found during any of the 
preflight checks or inspections of the aft cove panel of the wing 
required by paragraphs (a) and (b) of this AD, prior to further 
flight, accomplish the following:
    (1) Delamination (Debonding) Found During the Preflight Visual 
Checks Specified in the AFM Revisions Required by Paragraph (a) of 
This AD: In addition to the inspection required by paragraph (b) of 
this AD, incorporate one of the following:
    (i) Raytheon Field Repair drawing FR-SS-00010, Reinforcement of 
Aft cove panel of Flap Cove Assy P/N 122-100079-1/2, as referenced 
in Raytheon Safety Communique No. 158, dated March 1999; or
    (ii) Raytheon Kit 122-4019, Rev. B, dated March 12, 1999. This 
kit includes the procedures and parts necessary for modifying the 
attachment of the support rib at the center flap track.
    (2) Delamination (Debonding) Found During Any Inspection 
Required by Paragraph (b) of This AD: Incorporate Raytheon Kit 122-
4019, Rev. B, dated March 12, 1999. This kit includes the procedures 
and parts necessary for modifying the rib attachment center flap 
track.
    (d) Incorporating Raytheon Kit 122-4019, Rev. B, dated March 12, 
1999, as specified in paragraphs (c)(1)(ii) and (c)(2) of this AD 
constitutes terminating action for the AFM and repetitive inspection 
requirements of paragraphs (a) and (b) of this AD, respectively. 
This kit may be incorporated at any time, but must be incorporated 
if any delamination is found during any inspection required by 
paragraph (b) of this AD.
    (e) Incorporating the AFM temporary revisions as required by 
paragraph (a) of this AD may be performed by the owner/operator 
holding at least a private pilot certificate as authorized by 
Sec. 43.7 of the Federal Aviation Regulations (14 CFR 43.7), and 
must be entered into the aircraft records showing compliance with 
this AD in accordance with Sec. 43.9 of the Federal Aviation 
Regulations (14 CFR 43.9).
    (f) Special flight permits may be issued in accordance with 
Secs. 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 
inspections and modifications required by paragraphs (b) and (c) of 
this AD can be accomplished. The AFM temporary revisions required by 
paragraph (a) of this AD must be incorporated prior to this flight.
    (g) 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), 1801 Airport Road, Room 100, 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 ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

    (h) The inspections required by this AD shall be done in 
accordance with Raytheon Safety Communique No. 158, dated March 
1999. The modification required by this AD shall be done in 
accordance with Raytheon Field Repair drawing FR-SS-00010, Revision 
A, dated February 24, 1999, as referenced in Raytheon Safety 
Communique No. 158, dated March 1999; or Raytheon Field Service Kit 
122-4019, Revision B, dated March 12, 1999.

[[Page 24510]]

    (1) 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 the Raytheon Aircraft Company, 
P.O. Box 85, Wichita, Kansas 67201-0085.
    (2) Copies may be inspected at the FAA, Central Region, Office 
of the Regional 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.
    (i) This amendment becomes effective on June 3, 1999.

    Issued in Kansas City, Missouri, on April 29, 1999.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-11320 Filed 5-6-99; 8:45 am]
BILLING CODE 4910-13-U