[Federal Register Volume 64, Number 178 (Wednesday, September 15, 1999)]
[Proposed Rules]
[Pages 50018-50020]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-23996]
[[Page 50018]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-176-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Model BAe.125 Series 1000A and
1000B, and Model Hawker 1000 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 BAe.125 Series
1000A and 1000B, and Model Hawker 1000 series airplanes. This proposal
would require inspection of P1 pitot pipes for chafing or damage, and
various follow-on actions. This proposal is prompted by reports of P1
pitot pipes chafing against adjacent flight control cables. The actions
specified by the proposed AD are intended to prevent a hole in the P1
pitot pipes, which would lead to erroneous input to the instrumentation
and warning systems associated with the pilot's instruments.
DATES: Comments must be received by November 1, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-176-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, 9709 East Central, Wichita,
Kansas 67206. 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: Paul C. DeVore, Aerospace Engineer,
Systems and Propulsion Branch, ACE-116W, FAA, Small Airplane
Directorate, Wichita Aircraft Certification Office, 1801 Airport Road,
Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316)
946-4142; 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 99-NM-176-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-176-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received reports indicating that the P1 pitot pipes
have been found chafing against adjacent flight control cables on
Raytheon Model BAe.125 Series 1000A and 1000B, and Model Hawker 1000
series airplanes. Such chafing has been attributed to installation with
inadequate clearance during manufacture. This condition, if not
corrected, could wear a hole through the P1 pitot pipes, which would
result in erroneous input to the instrumentation and warning systems
associated with the pilot's instruments.
Explanation of Relevant Service Information
The FAA has reviewed and approved Raytheon Service Bulletin SB.34-
3028, dated January 1998, which describes procedures for inspection of
P1 pitot pipes for chafing or damage, and various follow-on actions. If
no chafing or damage is detected, follow-on actions consist of ensuring
that a minimum clearance of 0.25 inch exists between the flight control
cables and the adjacent P1 pitot pipes, and repositioning the P1 pitot
pipes as necessary to achieve this clearance. If any chafing or damage
is detected, follow-on actions include replacing discrepant parts with
new parts; ensuring that a minimum clearance of 0.25 inch exists
between the flight control cables and the adjacent P1 pitot pipes;
inspecting the flight control cables in the area of wear for damage;
and testing the P1 pitot system to ensure proper function.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified 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 require inspection of P1 pitot pipes for chafing or
damage, and replacement of discrepant parts with new parts; and
checking the installation to ensure a minimum clearance of 0.25 inch
exists between the flight control cables and the adjacent pipe, and
corrective actions, if necessary. If evidence of chafing is found, the
proposed AD also would require a test of the P1 pitot system to ensure
proper function, and inspection of the adjacent flight control cables
for any sign of damage. The actions would be required to be
accomplished in accordance with the service bulletin described
previously, except as discussed below.
If the test of the P1 pitot system fails, or if any damage to the
flight control cables is found, this proposed AD would require
corrective actions in accordance with the Aircraft Maintenance Manual.
Differences Between Proposed Rule and Service Bulletin
Operators should note that, although the service bulletin
recommends accomplishing the inspection of P1 pitot pipes for damage,
and follow-on actions, if necessary, during the next scheduled hourly
airframe inspection, the FAA has determined that a compliance time of
150 flight hours after the effective date of this AD for initiating the
required actions is warranted, in that it represents an appropriate
interval of time allowable for affected airplanes to
[[Page 50019]]
continue to operate without compromising safety. In developing an
appropriate compliance time for this AD, the FAA considered not only
the manufacturer's recommendation, but the degree of urgency associated
with addressing the subject unsafe condition, the average utilization
of the affected fleet, and the time necessary to perform the inspection
(one hour). The FAA finds that a compliance time of 150 flight hours
after the effective date of this AD would also closely correspond to
the time of the next scheduled hourly airframe inspection.
Cost Impact
There are approximately 52 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 39 airplanes of U.S. registry
would be affected by this proposed AD, that it would take approximately
1 work hour per airplane to accomplish the proposed inspection, 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 $2,340, or $60 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: Docket 99-NM-176-AD.
Applicability: All Model BAe.125 Series 1000A and 1000B, and
Model Hawker 1000 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 (b) 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, unless accomplished
previously.
To prevent a hole in the P1 pitot pipes, which would lead to
erroneous input to the instrumentation and warning systems
associated with the pilot's instruments, accomplish the following:
Inspections and Corrective Actions
(a) Within 150 flight hours after the effective date of this AD,
perform a one-time general visual inspection to detect chafing or
damage of the P1 pitot pipes, in accordance with Raytheon Service
Bulletin SB.34-3028, dated January 1998.
Note 2: For the purposes of this AD, a general visual inspection is
defined as: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or drop-light, and may require removal or opening of
access panels or doors. Stands, ladders, or platforms may be
required to gain proximity to the area being checked.''
(1) If no chafing or damage is found, prior to further flight,
ensure a clearance of 0.25 inch or more exists between the P1 pitot
pipes and flight control cables. If clearance is less than 0.25
inch, prior to further flight, reposition the P1 pitot pipes to
achieve 0.25-inch clearance, in accordance with the service
bulletin.
(2) If a pitot pipe is found to be chafed or damaged, prior to
further flight, accomplish the requirements of paragraphs (a)(2)(i),
(a)(2)(ii), and (a)(2)(iii) of this AD.
(i) Replace the discrepant pitot pipe with a new pipe, and
ensure that a clearance of 0.25 inch or more exists between the
flight control cables and the new pitot pipe, in accordance with the
service bulletin. If clearance is less than 0.25 inch, reposition
the P1 pitot pipes to achieve 0.25-inch clearance, in accordance
with the service bulletin.
(ii) Perform a general visual inspection for damage of the
flight control cables adjacent to the area of chafing or damage of
the P1 pitot pipes, in accordance with the service bulletin. If
damage is found, replace the damaged flight control cables with new
cables in accordance with Chapter 20-10-31 of the Aircraft
Maintenance Manual.
(iii) Perform a test of the P1 pitot system to ensure proper
function, in accordance with the service bulletin. If the P1 pitot
system fails the test, perform the corrective actions specified in
Chapter 34-11-00 of the Aircraft Maintenance Manual.
Alternative Methods of Compliance
(b) 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 Aircraft Certification
Office (ACO), FAA, Small Airplane Directorate. 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
(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.
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Issued in Renton, Washington, on September 8, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-23996 Filed 9-14-99; 8:45 am]
BILLING CODE 4910-13-P
