[Federal Register Volume 62, Number 34 (Thursday, February 20, 1997)]
[Proposed Rules]
[Pages 7731-7733]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-4197]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-NM-190-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Model DH 125-1A, -3A, and -
400A Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Raytheon Model DH 125-1A, -3A,
and -400A series airplanes. This proposal would 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 proposal is prompted by reports indicating that scoring
of the upper fuselage skin had been detected in that area. 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 March 31, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-190-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.
[[Page 7732]]
FOR FURTHER INFORMATION CONTACT: Larry Engler, Aerospace Engineer,
Airframe Branch, ACE-120W, FAA, Small Airplane Directorate, Wichita
Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4122; 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
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 96-NM-190-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-103, Attention: Rules
Docket No. 96-NM-190-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received reports indicating that scoring of the upper
fuselage skin around the periphery of the cockpit canopy blister
interface has occurred on Raytheon Model DH 125-1A, -3A, and -400A
series airplanes. Investigation revealed that the scoring was due to
the use of sharp instruments to remove excess sealant during the four-
year inspection cycle of the fuselage skin under the canopy blister.
Use of sharp instruments to remove excess sealant is contrary to the
instructions contained in Chapter 20 of the Airplane Maintenance Manual
(AMM). Scoring of the upper fuselage skin around the periphery of the
cockpit canopy blister interface, if not corrected, could result in
reduced structural integrity of the fuselage skin, and consequent cabin
depressurization.
Explanation of Relevant Service Information
The FAA has reviewed and approved Raytheon Service Bulletin SB.53-
93, dated May 16, 1996, which describes procedures for a one-time
detailed visual inspection to detect scoring of the upper fuselage skin
around the periphery of the cockpit canopy blister interface. The
service bulletin also describes repair procedures for scoring that is
within the specified limits.
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 require a one-time detailed visual inspection to
detect scoring of the upper fuselage skin around the periphery of the
cockpit canopy blister interface, and repair, if necessary. The visual
inspection and repair of scoring that is within certain limits would be
required to be accomplished in accordance with the service bulletin
described previously. Repair of scoring that is outside certain limits
would be required to be accomplished in accordance with a method
approved by the FAA.
Cost Impact
There are approximately 200 Model DH 125-1A, -3A, and -400A series
airplanes of the affected design in the worldwide fleet. The FAA
estimates that 115 airplanes of U.S. registry would be affected by this
proposed AD, that it would take approximately 4 work hours per airplane
to accomplish the proposed actions, and that the average labor rate is
$60 per work hour. Based on these figures, the cost impact of the
proposed AD on U.S. operators is estimated to be $27,600, or $240 per
airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the 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 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 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 adding the following new
airworthiness directive:
Raytheon Aircraft Company (Formerly Beech, Raytheon Corporate Jets,
British Aerospace, Hawker Siddeley, et al.): Docket 96-NM-190-AD.
Applicability: All Model DH 125-1A, -3A, and -400 series
airplanes, 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
[[Page 7733]]
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.
Note 2: Raytheon Model DH 125-1B, -3B, and -400B series
airplanes are similar in design to the airplanes that are subject to
the requirements of this AD and, therefore, also may be subject to
the unsafe condition addressed by this AD. However, as of the
effective date of this AD, those models are not type certificated
for operation in the United States. Airworthiness authorities of
countries in which the Model DH 125-1B, -3B, and -400B series
airplanes are approved for operation should consider adopting
corrective action, applicable to those models, that is similar to
the corrective action required by this AD.
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:
(a) 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 Service Bulletin SB.53-93,
dated May 16, 1996.
(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 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.
(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, 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.
(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.
Issued in Renton, Washington, on February 13, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-4197 Filed 2-19-97; 8:45 am]
BILLING CODE 4910-13-U
