AD 2000-07-13

[Federal Register Volume 65, Number 70 (Tuesday, April 11, 2000)]
[Rules and Regulations]
[Pages 19296-19298]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-8685]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-57-AD; Amendment 39-11667; AD 2000-07-13]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200 and -200PF Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 757-200 and -200PF series airplanes, 
that requires 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 
amendment also requires eventual replacement of the fuse pins with new 
corrosion resistant steel (CRES) fuse pins, which constitutes 
terminating action for the repetitive inspections. This amendment is 
prompted by a report of damaged fuse pins caused by corrosion. The 
actions specified by this 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: Effective May 16, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 16, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207.
    This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: James G. Rehrl, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2783; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Boeing Model 757-200 and -
200PF series airplanes was published in the Federal Register on October 
6, 1999 (64 FR 54227). That action proposed to 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. That action also proposed to 
require eventual replacement of the fuse pins with new corrosion 
resistant steel (CRES) fuse pins, which would constitute terminating 
action for the repetitive inspections.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.

Request To Change Repetitive Inspection Interval

    The commenter requests that the proposed repetitive inspection 
interval be changed from 3,000 flight cycles or 24 months (whichever 
occurs first) to either 36 months or to 3,000 flight cycles or 24 
months (whichever is later). The commenter states that 3,000 flight 
cycles does not correspond to the 24-month calendar time. The commenter 
adds that 36 months would more closely reflect the amount of time it 
takes for its airplanes to accumulate 3,000 flight cycles.
    The FAA does not concur with this request. This AD addresses 
corrosion of the fuse pins, which is a time-related phenomenon. 
Therefore, the critical element of the repetitive inspection interval 
in this case is the amount of calendar time that passes between 
inspections, rather than the number of flight cycles accumulated. 
Therefore, the FAA finds that the repetitive inspection interval of 
3,000 flight cycles or 24 months, whichever occurs first, is 
appropriate to address the identified unsafe condition in a timely 
manner and to ensure an adequate level of safety. No change to the 
final rule is necessary.

Revised Service Information

    Since the issuance of the proposed AD, the FAA has reviewed and 
approved Boeing Service Bulletin 757-57A0054, Revision 1, including 
Appendix A, both dated December 16, 1999. (The original issue of the 
service bulletin is referenced in the proposal as the appropriate 
source of service information for accomplishment of the actions 
required by this AD.) Revision 1 is essentially equivalent to the 
original issue; however, Revision 1 adds references to optional parts 
and changes certain compliance recommendations. Revision 1 recommends 
that, if the alloy steel fuse pins have already been replaced on an 
airplane that was four years (or more) old, the inspection of those 
pins can be extended to within four years or 6,000 flight cycles after 
installation. A new paragraph (b) has been added to the final rule to 
specify the revised compliance time for those particular airplanes.
    The FAA also has revised the final rule to include Revision 1 of 
the service bulletin as an additional source of service information. 
Further, the FAA has revised references to the original

[[Page 19297]]

issue of the service bulletin to include Appendix A, dated November 5, 
1998.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

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 
will be affected by this AD.
    It will take approximately 1 work hour per airplane to accomplish 
the required inspection, and that the average labor rate is $60 per 
work hour. Based on these figures, the cost impact of the inspection 
required by this AD on U.S. operators is estimated to be $21,000, or 
$60 per airplane, per inspection cycle.
    It will take approximately 440 work hours per airplane to 
accomplish the required 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 AD. Based on these 
figures, the cost impact of the replacement required by this 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 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 adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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, Incorporation by 
reference, 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 the following new 
airworthiness directive:

2000-07-13  Boeing: Amendment 39-11667. 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 (e) 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, including Appendix A, dated November 5, 1998, or Boeing 
Service Bulletin 757-57A0054, Revision 1, including Appendix A, 
dated December 16, 1999; 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 
(d) 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.''

    (b) For airplanes on which the alloy steel fuse pins were 
replaced prior to the effective date of this AD: Perform the initial 
inspection required by paragraph (a) of this AD within 4 years or 
6,000 flight cycles after installation of the pins, whichever occurs 
later. Thereafter, accomplish the repetitive inspections required by 
paragraph (a) of this AD at the time specified in that paragraph.

Corrective Action

    (c) 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, including Appendix A, dated November 5, 1998, or Boeing 
Service Bulletin 757-57A0054, Revision 1, including Appendix A, 
dated December 16, 1999. 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

    (d) 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, including Appendix 
A, dated November 5, 1998, or Boeing Service Bulletin 757-57A0054, 
Revision 1, including Appendix A, dated December 16, 1999. 
Accomplishment of the action specified in this paragraph constitutes 
terminating action for the repetitive inspection requirements of 
this AD.

Alternative Methods of Compliance

    (e) 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,

[[Page 19298]]

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

    (f) 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.

Incorporation by Reference

    (g) The actions shall be done in accordance with Boeing Alert 
Service Bulletin 757-57A0054, including Appendix A, dated November 
5, 1998, or Boeing Service Bulletin 757-57A0054, Revision 1, 
including Appendix A, dated December 16, 1999. This incorporation by 
reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, 
Seattle, Washington 98124-2207. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.
    (h) This amendment becomes effective on May 16, 2000.

    Issued in Renton, Washington, on April 3, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-8685 Filed 4-10-00; 8:45 am]
BILLING CODE 4910-13-U