AD 2002-24-02

[Federal Register Volume 67, Number 232 (Tuesday, December 3, 2002)]
[Rules and Regulations]
[Pages 71810-71812]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-30342]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-192-AD; Amendment 39-12967; AD 2002-24-02]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200 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 series airplanes, that 
requires repetitive inspections for fatigue cracking of certain areas 
of the forward and aft frames of the cargo doorways and repair, if 
necessary. The actions specified by this AD are intended to find and 
fix such cracking, which could lead to rapid depressurization of the 
airplane and result in reduced structural integrity of the cargo 
doorway. This action is intended to address the identified unsafe 
condition.

DATES: Effective January 7, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 7, 2003.

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: Dennis Stremick, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2776; 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 
series airplanes was published in the Federal Register on July 12, 2002 
(67 FR 46132). That action proposed to require repetitive inspections 
for fatigue cracking of certain areas of the forward and aft frames of 
the cargo doorways, and repair, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received. One commenter states that the proposed AD does 
not apply to its fleet.

Request To Change Certain Terminology

    One commenter states that the terminology throughout the proposed 
AD which reads, ``cargo door frame(s)'' should be changed to ``cargo 
doorway frames.'' The commenter notes that the structures requiring the 
inspections are the cutout fuselage frames of the cargo door and not 
the cargo door frames. The commenter adds that the term ``cargo 
doorway,'' as specified in Boeing Alert Service Bulletin 757-53A0080, 
dated February 3, 2000 (referenced in the proposed AD as the 
appropriate source of service information for accomplishment of the 
actions), is a better description.
    We agree with the commenter in that the description of the frames 
of the cargo door should be clarified. We have changed the description 
throughout this final rule to read, ``cargo doorway.''

Explanation of Editorial Change

    We have changed the service bulletin citation throughout this final 
rule to exclude the Evaluation Form. (The form is intended to be 
completed by operators and submitted to the

[[Page 71811]]

manufacturer to provide input on the quality of the service bulletin; 
however, this AD does not include such a requirement.)

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing a modification that will 
address the unsafe condition identified in this AD. Once this 
modification is developed, approved, and available, the FAA may 
consider further rulemaking.

Cost Impact

    There are approximately 57 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 28 airplanes of U.S. registry 
will be affected by this AD.
    For all airplanes: It will take approximately 3 work hours per 
airplane to do the high frequency eddy current and detailed 
inspections, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the inspections required by this AD 
on U.S. operators is estimated to be $5,040, or $180 per airplane, per 
inspection cycle.
    For Group 3 airplanes: It will take approximately 1 work hour per 
airplane to do the additional detailed inspection, at an average labor 
rate of $60 per work hour. Based on these figures, the cost impact of 
this required inspection on U.S. operators is estimated to be $60 per 
airplane, per inspection cycle.
    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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

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:

2002-24-02 Boeing: Amendment 39-12967. Docket 2001-NM-192-AD.

    Applicability: Model 757-200 series airplanes, line numbers 1 
through 57 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 (c) 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 find and fix fatigue cracking of the cargo doorway frames, 
which could lead to rapid depressurization of the airplane and 
result in reduced structural integrity of the cargo doorway, 
accomplish the following:

Repetitive Inspections

    (a) Before the accumulation of 22,000 total flight cycles or 
within 500 flight cycles after the effective date of this AD, 
whichever is later: Do the applicable inspections specified in 
paragraphs (a)(1) and (a)(2) of this AD, per Boeing Alert Service 
Bulletin 757-53A0080, excluding Evaluation Form, dated February 3, 
2000.
    (1) For all airplanes: Do detailed and high frequency eddy 
current (HFEC) inspections for cracking of the doorway frames of the 
number 1 and 2 cargo doors (includes the frame webs, frame inner and 
outer chords, bear strap, and skin panels between the upper and 
lower sills of the cargo doorway). Repeat the detailed inspections 
every 3,000 flight cycles, and the HFEC inspections every 12,000 
flight cycles.
    (2) For Group 3 airplanes: Do a detailed inspection for cracking 
of the doorway frame of the number 3 cargo door. Repeat the 
inspection every 3,000 flight cycles.

    Note 2: For the purposes of this AD, a detailed 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.''

Repair

    (b) Before further flight, repair any cracking found in the 
frame webs, per Boeing Alert Service Bulletin 757-53A0080, excluding 
Evaluation Form, dated February 3, 2000. If any cracking is found in 
any other area and the service bulletin specifies to contact Boeing 
for disposition of those repairs, repair per a method approved by 
the Manager, Seattle Aircraft Certification Office (ACO), FAA; or 
per data meeting the type certification basis of the airplane 
approved by a Boeing Company Designated Engineering Representative 
(DER) who has been authorized by the Manager, Seattle ACO, to make 
such findings. For a repair method to be approved, the approval must 
specifically reference this AD.

    Note 3: There is no terminating action currently available for 
the repetitive inspections required by this AD.

Alternative Methods of Compliance

    (c) An alternative method of compliance or adjustment of the 
compliance time that

[[Page 71812]]

provides an acceptable level of safety may be used if approved by 
the Manager, Seattle ACO. 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 4: 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

    (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 airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (e) Except as provided by paragraph (b) of this AD, the actions 
shall be done per Boeing Alert Service Bulletin 757-53A0080, 
excluding Evaluation Form, dated February 3, 2000. 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.

Effective Date

    (f) This amendment becomes effective on January 7, 2003.

    Issued in Renton, Washington, on November 20, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-30342 Filed 12-2-02; 8:45 am]
BILLING CODE 4910-13-P