[Federal Register Volume 65, Number 117 (Friday, June 16, 2000)]
[Proposed Rules]
[Pages 37723-37725]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-15310]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-345-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model BH.125, DH.125, and 
HS.125 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to all Raytheon Model DH.125-
1A, -3A, and -400A series airplanes, that currently requires a one-time 
inspection to detect scoring of the upper fuselage skin around the 
periphery of the cockpit canopy blister interface, and repair, if 
necessary. This action would expand the applicability of the existing 
AD to include additional airplanes, and would require that the actions 
be accomplished in accordance with revised service information for the 
newly added airplanes. This AD is prompted by additional reports 
indicating that scoring has been detected on the upper fuselage skin 
around the periphery of the cockpit canopy blister interface. The 
actions specified by the proposed AD are intended to detect and correct 
scoring of the upper fuselage skin around the periphery of the cockpit 
canopy blister interface, which could result in reduced structural 
integrity of the fuselage, and consequent cabin depressurization.

DATES: Comments must be received by July 31, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-345-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Raytheon Aircraft Company, Commercial Service Department, 
P.O. Box 85, Wichita, Kansas 67201-0085. This information may be 
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, 
SW., Renton, Washington; or at the FAA, Small Airplane Directorate, 
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, 
Mid-Continent Airport, Wichita, Kansas.

FOR FURTHER INFORMATION CONTACT: T.N. Baktha, Aerospace Engineer, 
Airframe Branch, ACE-118W, FAA, Small Airplane Directorate, Wichita 
Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4155; fax 
(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 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

[[Page 37724]]

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 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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-345-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. 99-NM-345-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On April 24, 1997, the FAA issued AD 97-09-12, amendment 39-10008 
(62 FR 24013, May 2, 1997), applicable to all Raytheon Model DH.125-1A, 
-3A, and -400A series airplanes, to require a one-time inspection to 
detect scoring of the upper fuselage skin around the periphery of the 
cockpit canopy blister interface, and repair, if necessary. That action 
was prompted by reports indicating that scoring of the upper fuselage 
skin had been detected in the area. The requirements of that AD are 
intended to detect and correct scoring of the upper fuselage skin 
around the periphery of the cockpit canopy blister interface, which 
could result in reduced structural integrity of the fuselage, and 
consequent cabin depressurization.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, the FAA has received numerous 
reports indicating that scoring has been detected on the upper fuselage 
skin around the periphery of the cockpit canopy blister interface. 
Investigation revealed that the scoring was caused by the use of an 
improper tool (Exacto knife), which was used to remove excess sealant 
along the interface of the fuselage skin and the cockpit canopy. In 
light of these additional reports, the FAA has determined that certain 
Raytheon Model BH.125, DH.125, and HS.125 series airplanes may be 
subject to the identified unsafe condition.

Issuance of Revised Service Information

    The FAA has reviewed and approved Raytheon Aircraft Service 
Bulletin SB 53-93, Revision 2, dated April 2000. The inspection and 
repair procedures described in this revision are identical to those 
described in the original issue of the service bulletin (which is 
referenced in AD 97-09-12). However, this revision expands the 
effectivity listing to include additional airplanes that are subject to 
the addressed unsafe condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would supersede AD 97-09-12 to continue to require a one-
time inspection to detect scoring of the upper fuselage skin around the 
periphery of the cockpit canopy blister interface, and repair, if 
necessary. This action would expand the applicability of the existing 
AD to include additional airplanes that may also be subjected to the 
identified unsafe condition. The actions would be required to be 
accomplished in accordance with the service bulletin described 
previously.

Cost Impact

    There are approximately 290 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 200 airplanes of U.S. registry 
would be affected by this proposed AD.
    The actions that are currently required by AD 97-09-12 and retained 
in this proposed AD would take approximately 4 work hours per airplane 
to accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators is estimated to be $48,000, or $240 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.

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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-10008 (62 FR 
24013, May 2, 1997), and by adding a new airworthiness directive (AD), 
to read as follows:

Raytheon Aircraft Company: Docket 99-NM-345-AD. Supersedes AD 97-09-
12, Amendment 39-10008.

    Applicability: Model DH.125, BH.125, and HS.125 series airplanes 
as listed in Raytheon Aircraft Service Bulletin SB 53-93, Revision 
2, dated April 2000; 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

[[Page 37725]]

been eliminated, the request should include specific proposed 
actions to address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct scoring of the upper fuselage skin around 
the periphery of the cockpit canopy blister interface, which could 
result in reduced structural integrity of the fuselage skin, and 
consequent cabin depressurization; accomplish the following:

Restatement of the Requirements of AD 97-09-12

    (a) For Model DH.125-1A, -3A, and -400A series airplanes as 
identified in Raytheon Aircraft Service Bulletin SB 53-93, dated May 
16, 1996: Within 90 days after June 6, 1997 (the effective date of 
AD 97-09-12, amendment 39-10008), perform a one-time detailed visual 
inspection to detect scoring of the upper fuselage skin around the 
periphery of the cockpit canopy blister interface, in accordance 
with the service bulletin.
    (b) If no scoring is detected during the inspection required by 
paragraph (a) of this AD, no further action is required by this AD.
    (c) If any scoring is detected during the inspection required by 
paragraph (a) of this AD, prior to further flight, determine the 
maximum location and details of each score, including the edge 
distance and material thickness, in accordance with Raytheon 
Aircraft Service Bulletin SB 53-93, dated May 16, 1996.
    (1) If any scoring is found that is within the limits specified 
in the service bulletin, prior to further flight, repair in 
accordance with the service bulletin.
    (2) If any scoring is found that is outside the limits specified 
in the service bulletin, prior to further flight, repair in 
accordance with a method approved by the Manager, Wichita Aircraft 
Certification Office (ACO), FAA, Small Airplane Directorate.

New Requirements of This AD

    (d) For airplanes identified in Raytheon Aircraft Service 
Bulletin SB 53-93, Revision 2, dated April 2000, and not previously 
identified in paragraph (a) of this AD: Within 90 days after the 
effective date of this AD, perform a one-time detailed visual 
inspection to detect scoring of the upper fuselage skin around the 
periphery of the cockpit canopy blister interface, in accordance 
with Raytheon Aircraft Service Bulletin SB 53-93, Revision 2, dated 
April 2000.
    (1) If no scoring is detected during the inspection required by 
paragraph (d) of this AD, no further action is required by this AD.
    (2) If any scoring is detected during the inspection required by 
paragraph (d) of this AD, prior to further flight, determine the 
location and details of each score, including the edge distance and 
material thickness, in accordance with the service bulletin.
    (i) If any scoring is found that is within the limits specified 
in the service bulletin, prior to further flight, repair in 
accordance with the service bulletin.
    (ii) If any scoring is found that is outside the limits 
specified in the service bulletin, prior to further flight, repair 
in accordance with a method approved by the Manager, Wichita ACO.

    Note 2: Any inspections and repairs accomplished prior to the 
effective date in accordance with Raytheon Service Bulletin SB 53-
93, Revision 1, dated April 1999, are considered acceptable for 
compliance for the applicable actions 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, Wichita ACO. Operators shall submit 
their requests through an appropriate FAA Principal 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.

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.

    Issued in Renton, Washington, on June 12, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-15310 Filed 6-15-00; 8:45 am]
BILLING CODE 4910-13-U