[Federal Register Volume 64, Number 193 (Wednesday, October 6, 1999)]
[Proposed Rules]
[Pages 54227-54228]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25936]


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 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. 193 / Wednesday, October 6, 1999 / 
Proposed Rules  

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-57-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200 and -200PF 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 certain Boeing Model 757-200 and -
200PF series airplanes. This proposal would require repetitive detailed 
visual inspections to detect loose fuse pins in the outboard beam 
attachment and forward trunnion support on the main landing gear (MLG) 
and to detect corrosion on the structure adjacent to the fuse pin; and 
corrective actions, if necessary. This proposal also would require 
eventual replacement of the fuse pins with new corrosion resistant 
steel (CRES) fuse pins, which would constitute terminating action for 
the repetitive inspections. This proposal is prompted by a report of 
damaged fuse pins caused by corrosion. The actions specified by the 
proposed AD are intended to prevent corroded fuse pins, which could 
result in the MLG separating from the wing, and consequent damage to 
the airplane and possible rupture of the wing fuel tank.

DATES: Comments must be received by November 22, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-57-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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Rick Kawaguchi, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-1153; fax (425) 227-1181.

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-57-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-57-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received a report indicating that, during heavy 
maintenance of several Boeing Model 757-200 series airplanes, 28 fuse 
pins were found damaged due to corrosion. Fuse pins made from 4330M and 
4340 alloy with cracks in the chrome plating can be damaged by 
corrosion. Such corrosion or cracking, if not corrected, could result 
in the main landing gear (MLG) separating from the wing, and consequent 
damage to the airplane and possible rupture of the wing fuel tank.
    The subject fuse pins on Boeing Model 757-200PF series airplanes 
are identical to those on the affected Boeing Model 757-200 series 
airplanes. Therefore, both of these airplanes may be subjected to the 
same unsafe condition.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
757-57A0054, dated November 5, 1998, which describes procedures for 
repetitive detailed visual inspections to detect loose fuse pins in the 
outboard beam attachment and forward trunnion support on the MLG and 
corrosion on the structure adjacent to the fuse pin; and corrective 
actions, if necessary. The corrective actions involve performing a 
detailed visual inspection to detect corrosion on the fuse pin's mating 
parts, and repairing the parts, if necessary; performing a detailed 
visual inspection to detect cracks on the outer surface of the fuse pin 
chrome plating; and replacing the alloy steel fuse pins with new 
corrosion resistant steel (CRES) fuse pins, which would eliminate the 
need for the repetitive inspections. The service bulletin also 
describes procedures for a terminating action for the repetitive 
inspections. Accomplishment of the action 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 accomplishment of the actions

[[Page 54228]]

specified in the service bulletin described previously.

Cost Impact

    There are approximately 805 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 350 airplanes of U.S. registry 
would be affected by this proposed AD.
    It would take approximately 1 work hour per airplane to accomplish 
the proposed inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the inspection proposed by 
this AD on U.S. operators is estimated to be $21,000, or $60 per 
airplane, per inspection cycle.
    It would take approximately 440 work hours per airplane to 
accomplish the proposed replacement, at an average labor rate of $60 
per work hour. The manufacturer has committed previously to its 
customers that it will bear the cost of replacement parts. As a result, 
the cost of those parts are not attributable to this proposed AD. Based 
on these figures, the cost impact of the proposed AD on U.S. operators 
is estimated to be $9,240,000, or $26,400 per airplane.
    The cost impact figures discussed above are 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:

Boeing: Docket 99-NM-57-AD.

    Applicability: Model 757-200 and -200PF series airplanes, line 
numbers 1 through 806 inclusive; 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 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 corroded fuse pins, which could result in the main 
landing gear (MLG) separating from the wing, and consequent damage 
to the airplane and possible rupture of the wing fuel tank, 
accomplish the following:

Repetitive Inspections

    (a) Perform a detailed visual inspection to detect loose fuse 
pins in the outboard beam attachment and forward trunnion support on 
the MLG and to detect corrosion on the structure adjacent to the 
fuse pin, in accordance with Boeing Alert Service Bulletin 757-
57A0054, dated November 5, 1998; at the later of the times specified 
in paragraphs (a)(1) and (a)(2) of this AD. Thereafter, repeat the 
inspection at intervals not to exceed 3,000 flight cycles or 24 
months, whichever occurs first, until accomplishment of paragraph 
(c) of this AD.
    (1) Prior to 4 years since date of manufacture of the airplane; 
or
    (2) Within 3,000 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

Corrective Action

    (b) If any loose fuse pin or corrosion on the structure adjacent 
to the fuse pin is detected during any inspection required by 
paragraph (a) of this AD, prior to further flight, perform the 
applicable corrective action [i.e., detailed visual inspections for 
cracks or corrosion, repair of discrepant parts, and replacement of 
fuse pin] in accordance with Boeing Alert Service Bulletin 757-
57A0054, dated November 5, 1998. Replacement of an alloy steel fuse 
pin with a new corrosion resistant steel (CRES) fuse pin constitutes 
terminating action for the repetitive inspection requirements of 
paragraph (a) of this AD for that fuse pin only.

Terminating Action

    (c) At the next scheduled MLG overhaul, or within 12 years after 
the effective date of this AD, whichever occurs first, replace all 
alloy steel fuse pins with new CRES fuse pins in the outboard beam 
attachment and forward trunnion support on the MLG in accordance 
with Boeing Alert Service Bulletin 757-57A0054, dated November 5, 
1998. Accomplishment of the action specified in this paragraph 
constitutes terminating action for the repetitive inspection 
requirements of this AD.

Alternative Methods of Compliance

    (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, Seattle Aircraft Certification 
Office (ACO), FAA, Transport 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, Seattle ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (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 September 29, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-25936 Filed 10-5-99; 8:45 am]
BILLING CODE 4910-13-U