[Federal Register Volume 64, Number 169 (Wednesday, September 1, 1999)]
[Proposed Rules]
[Pages 47715-47717]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-22774]


 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 64, No. 169 / Wednesday, September 1, 1999 / 
Proposed Rules  

[[Page 47715]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-33-AD]


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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to revise an existing airworthiness 
directive (AD), 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, that currently requires an inspection to ensure the 
locking mechanism is engaging properly, and replacing the buckle-half 
of the seat restraint system, if necessary. This action would allow an 
owner/operator (pilot) to determine if the locking mechanism is 
engaging properly, but would still require replacing the buckle-half of 
the seat restraint system, if necessary. This proposal is prompted by a 
determination made by the FAA that pilots may perform the one-time 
check, and that only affected seat restraint systems manufactured 
between March, 1997 and November, 1998 need to be checked. The actions 
specified by the proposed 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: Comments must be received by November 1, 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. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.

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:

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 should 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 No. 98-SW-33-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, Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-33-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

Discussion

    On December 3, 1998, the FAA issued AD 98-25-10, Amendment 39-10936 
(63 FR 67775, December 9, 1998), to require, 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. That action was prompted by manufacturer's 
reports of two failures of the seat restraint system that occurred in 
the field. That condition, if not corrected, could result in the seat 
restraint system failing to properly secure the occupant during 
turbulence or landing. Since the issuance of that AD, the FAA has re-
evaluated its previous position and determined that ensuring the 
locking mechanism is engaging properly may be accomplished by a pilot. 
Additionally, since the issuance of that AD, the manufacturer has 
notified the FAA that only model-numbered seat restraint systems 
manufactured between March, 1997 and November, 1998 are affected, as 
opposed to those same model-numbered seat restraint systems 
manufactured during other years. In December, 1998, the FAA received a 
comment requesting the inclusion of the address of the manufacturer so 
that defective buckles could be returned for replacement. Defective 
buckles should be sent to Aircraft Belts, Inc., 2000 Anders Lane, 
Kemah, Texas 77565.
    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, the proposed AD would revise 
AD 98-25-10 to require, within 10 hours TIS, a check to ensure the 
locking mechanism is engaging properly, and replacing the buckle-half 
of the seat restraint system, if necessary. The visual check required 
by this AD may be performed by an owner/operator (pilot), but must be 
entered into the aircraft records showing compliance

[[Page 47716]]

with this AD in accordance with sections 43.11 and 91.417(a)(2)(v) of 
the Federal Aviation Regulations (14 CFR sections 43.11 and 
91.417(a)(2)(v)). This AD allows a pilot to perform this check because 
it involves only a visual check to ensure the locking mechanism is 
engaging properly and also allows a pilot to replace any buckle half 
since it is such a simple procedure.
    The FAA estimates that 12,278 seat restraint systems would be 
affected by this proposed AD, that it would take approximately one-half 
work hour to accomplish the proposed actions, and that the average 
labor rate is $60 per work hour. Required parts would cost 
approximately $10 per buckle half. The manufacturer has stated that it 
will provide the buckle half to owner/operators at no cost. Based on 
these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $368,340.
    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), 40114, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-10936 (63 FR 
67775, December 9, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:

Aircraft Belts, Inc.: Docket No. 98-SW-33-AD. Revises AD 98-25-10, 
Amendment 39-10936.

    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 
manufactured between March 1997 and November 1998 that are 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 otherwise 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 request approval for an alternative method of 
compliance in accordance with paragraph (d) 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 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 check 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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[GRAPHIC] [TIFF OMITTED] TP01SE99.011



BILLING CODE 4910-13-C
    (b) If the locking mechanism does not seat properly, replace the 
buckle with an airworthy buckle.
    (c) The requirements of this AD may be performed by an owner/
operator (pilot) holding at least a private pilot certificate, and 
must be entered into the aircraft records showing compliance with 
this AD in accordance with Secs. 43.11 and 91.417(a)(2)(v) of the 
Federal Aviation Regulations (14 CFR sections 43.11 and 
91.417(a)(2)(v)).

    Note 3: If the seat restraint systems' locking mechanisms are 
found to be functioning properly after the visual check described in 
paragraph (a) of this AD, the following is an example of a 
maintenance record entry that may be used:

    ``AD (number), paragraph (a) complied with by visual check. Seat 
belt buckle locking mechanism(s) found serviceable. (Date) (Aircraft 
total time-in-service). (Signature) (Certificate number and type of 
certificate held)''
    If any of the seat restraint systems' locking mechanisms are 
found to malfunction after the visual check described in paragraph 
(a), the following is an example of a maintenance record entry that 
may be used:
    ``AD (number), paragraphs (a) and (b) complied with by visual 
check and replacement of seat belt buckle locking mechanism(s) on 
(seat location(s)) with airworthy buckle(s). (Date) (Aircraft total 
time-in-service). (Signature) (Certificate number and type of 
certificate held)''
    (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, Airplane Certification Office, FAA. 
Operators shall submit their requests through a FAA Principal 
Maintenance Inspector, who may concur or comment and then send it to 
the Manager, Airplane Certification Office.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Airplane Certification Office.

    (e) Special flight permits may be issued in accordance with 
Secs. 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.

    Issued in Fort Worth, Texas, on July 27, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-22774 Filed 8-31-99; 8:45 am]
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