AD Amdt-39-10936

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-32619]


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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.

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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.

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    (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]
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