[Federal Register Volume 63, Number 236 (Wednesday, December 9, 1998)]
[Rules and Regulations]
[Pages 67775-67778]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-32619]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-33-AD; Amendment 39-10936; AD 98-25-10]
RIN 2120-AA64
Airworthiness Directives; Aircraft Belts, Inc. Model CS, CT, FM,
FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH Seat
Restraint Systems
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD,
JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint
systems, installed on, but not limited to, Beech Aircraft Corp., Bell
Helicopter Textron, Inc., Cessna Aircraft Co., Dassault Aviation,
Eurocopter Deutschland, Eurocopter France, Gulfstream Aerospace,
Learjet Corp., Lockheed Aircraft Corp., and Piper Aircraft Corp.
aircraft. This action requires an inspection to ensure the locking
mechanism is engaging properly, and replacing the buckle-half of the
seat restraint system, if necessary. This amendment is prompted by the
manufacturer reporting two failures of the seat restraint system in the
field. The actions specified in this AD are intended to prevent failure
of the seat restraint system due to the buckle assembly locking
mechanism not engaging properly, which could result in the seat
restraint system failing to properly secure the occupant during
turbulence or landing.
DATES: Effective December 24, 1998.
Comments for inclusion in the Rules Docket must be received on or
before February 8, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-33-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Rob Romero, Aerospace Engineer,
Airplane Certification Office, ASW-150, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137, telephone (817) 222-5102, fax (817) 222-5960.
SUPPLEMENTARY INFORMATION: This amendment adopts a new AD that is
applicable to Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD,
JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint
systems installed on, but not limited to, Beech Aircraft Corp., Bell
Helicopter Textron, Inc., Cessna Aircraft Co., Dassault Aviation,
Eurocopter Deutschland, Eurocopter France, Gulfstream Aerospace,
Learjet Corp., Lockheed Aircraft Corp., and Piper Aircraft Corp.
aircraft. This action requires, within 10 hours time-in-service (TIS),
a one-time inspection to ensure the locking mechanism is engaging
properly, and replacing the buckle-half of the seat restraint system,
if necessary. This amendment is prompted by manufacturer's reports of
two failures of the seat restraint system that occurred in the field.
The actions specified in this AD are intended to prevent failure of the
seat restraint system due to the buckle assembly locking mechanism not
engaging properly, which could result in the seat restraint system
failing to properly secure the occupant during turbulence or landing.
The FAA has reviewed Aircraft Belts, Inc. Service Bulletin dated
June 16, 1998, which describes procedures for inspecting the buckle
assembly on certain restraint systems to ensure the locking mechanism
engages properly.
Since an unsafe condition has been identified that is likely to
exist or develop on other Aircraft Belts, Inc. Model CS, CT, FM, FN,
GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat
restraint systems of the same type design, this AD is being issued to
prevent failure of the seat restraint system due to the buckle assembly
locking mechanism not engaging properly, which could result in the seat
restraint system failing to properly secure the occupant during
turbulence or landing. This AD requires, within 10 hours TIS, a one-
time inspection to ensure the seat restraint system locking mechanism
is engaging properly, and replacing the buckle-half of the seat
restraint system, if necessary. The short compliance time involved is
required because the previously described critical unsafe condition can
adversely affect the controllability of the aircraft. Therefore, the
one-time inspection and replacement, if necessary, is required within
10 hours TIS, and this AD must be issued immediately.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
[[Page 67776]]
Cost Impact
The FAA estimates that 12,278 seat restraint systems will be
affected by this proposed AD, that it will take approximately one-half
work hour per seat restraint system to accomplish the inspection and
replacement (if necessary), and that the average labor rate is $60 per
work hour. Replacement parts will cost $10 per buckle half. However,
the manufacturer has stated that it will provide the buckle half to
owners/operators at no cost. Based on these figures, the total cost
impact of the AD on U.S. operators is estimated to be $368,340.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public 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 under the caption ADDRESSES. 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 Docket No. 98-SW-33-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 that it 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.
A copy of it, if filed, may be obtained from 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.
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
to read as follows:
AD 98-25-10 Aircraft Belts, Inc.: Amendment 39-10936. Docket No.
98-SW-33-AD.
Applicability: Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD,
ME, MM, MN, NB, PM, PN, RG, and RH seat restraint systems installed
on, but not limited to, Beech Aircraft Corp., Bell Helicopter
Textron, Inc., Cessna Aircraft Co., Dassault Aviation, Eurocopter
Deutschland, Eurocopter France, Gulfstream Aerospace, Learjet Corp.,
Lockheed Aircraft Corp., and Piper Aircraft Corp. aircraft,
certificated in any category.
Note 1: This AD applies to each seat restraint system 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 seat restraint systems that have been
modified, altered, or repaired so that the performance of the
requirements of this AD is affected, the owner/operator must use the
authority provided in paragraph (c) to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition, or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any seat restraint system from the applicability of this AD.
Compliance: Required within 10 hours time-in-service after the
effective date of this AD, unless accomplished previously.
To prevent failure of the seat restraint system due to the
buckle assembly (buckle) locking mechanism not engaging properly,
which could result in the seat restraint system failing to properly
secure the occupant during turbulence or landing, accomplish the
following:
Note 2: The part number (P/N) of the seat restraint system is on
the identification label located on each end of the seat restraint
system near the anchor point (Example: P/N MD A2626-E010). The model
is designated by the first two letters of the P/N.
(a) Visually inspect all affected seat restraint systems to
determine if the locking mechanism is engaging properly in
accordance with the following:
(1) Open the lift lever of the buckle fully until it will not
open any further. This will cause the locking mechanism to pivot on
the pivot pin.
(2) Allow the spring to close the lift lever slowly until the
lift lever is back to its at-rest position.
(3) After the lever is completely closed, examine the slot in
the bottom of the buckle. The locking mechanism should be firmly
seated against the edge of the slot as shown in Figure 1.
BILLING CODE 4910-13-P
[[Page 67777]]
[GRAPHIC] [TIFF OMITTED] TR09DE98.044
BILLING CODE 4910-13-C
[[Page 67778]]
(b) If the locking mechanism does not seat properly, replace the
buckle with an airworthy buckle.
(c) 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, Airplane Certification Office, FAA.
Operators shall submit their requests through an FAA Principal
Maintenance Inspector, who may concur or comment and then send it to
the Manager, Airplane Certification Office.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Airplane Certification Office.
(d) 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 aircraft to a location where
the requirements of this AD can be accomplished.
(e) This amendment becomes effective on December 24, 1998.
Issued in Fort Worth, Texas, on December 3, 1998.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-32619 Filed 12-8-98; 8:45 am]
BILLING CODE 4910-13-P
