[Federal Register Volume 66, Number 10 (Tuesday, January 16, 2001)]
[Proposed Rules]
[Pages 3521-3523]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-1235]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-303-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777-200 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 777-200 
series airplanes. This proposal would require repetitive detailed 
visual and ultrasonic inspections of the lower flange of the flaperon 
inboard support to find cracking, and corrective actions, if necessary. 
This proposal also would require a modification, which would terminate 
the repetitive inspections. This action is necessary to prevent 
fracture of the inboard support structure, which could result in an in-
flight loss of the inboard flaperon, structural damage, and consequent 
reduced controllability of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Comments must be received by March 2, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-303-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 

<a href="/cdn-cgi/l/email-protection#f9c0d4989794d497898b949a9694949c978db99f9898d79e968f"><span class="__cf_email__" data-cfemail="4f76622e212262213f3d222c2022222a213b0f292e2e61282039">[email protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-303-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    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: Stan Wood, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2772; 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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
    <bullet> Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    <bullet> For each issue, state what specific change to the proposed 
AD is being requested.
    <bullet> Include justification (e.g., reasons or data) for each 
request.
    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-303-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. 2000-NM-303-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    Flight testing of certain Boeing Model 777-200 series airplanes 
showed that high engine thrust conditions during takeoff cause 
tremendous cyclic loads on the support structure of the inboard 
flaperon. Based on engineering analysis, fatigue cracks of the support 
structure could develop at approximately 4,000 flight cycles. Such 
fatigue cracking could result in fracture of the inboard support 
structure, in-flight loss of the inboard flaperon, significant damage 
to the surrounding structure, and consequent reduced controllability of 
the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
777-57A0036, dated June 24, 1999, which describes procedures for 
detailed visual and ultrasonic inspections of the lower flange of the 
flaperon inboard support to find cracking, and corrective actions if 
cracking is found. The corrective actions consist of accomplishment of 
the terminating action in Part 2 of the service bulletin. The 
terminating action includes, but is not limited to, a high frequency 
eddy current inspection to find cracks of the aft holes that attach the 
failsafe strap to the lower flange, oversizing of the holes if cracks 
are found, and installation of a failsafe strap. Accomplishment of the 
actions 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 3522]]

specified in the service bulletin described previously, except as 
discussed below.

Differences Between Service Bulletin and This Proposed AD

    While the effectivity listing of the service bulletin includes 
airplanes having line numbers (L/N) 2 through 9 inclusive; this 
proposed AD would apply to airplanes having L/N's 1 through 9 
inclusive. The FAA has determined that the subject area on the airplane 
with L/N 1 is identical to the subject areas on the Model 777-200 
series airplanes listed in the service bulletin; so the airplane with 
L/N 1 is also subject to the identified unsafe condition.
    Although the service bulletin specifies that the manufacturer may 
be contacted for instructions on repair of certain conditions, this 
proposed AD would require the repair of those conditions to be 
accomplished per a method approved by the FAA, or per data meeting the 
type certification basis of the airplane approved by a Boeing Company 
Designated Engineering Representative who has been authorized by the 
FAA to make such findings.

Cost Impact

    There are approximately 9 airplanes of the affected design in the 
worldwide fleet.
    The FAA estimates that 1 airplane of U.S. registry would be 
affected by this proposed AD.
    It would take approximately 3 work hours per airplane to accomplish 
the proposed inspections, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of the inspections 
proposed by this AD on U.S. operators is estimated to be $180 per 
airplane, per inspection cycle.
    It would take approximately 6 work hours per airplane to accomplish 
the proposed terminating action, at an average labor rate of $60 per 
work hour. Required parts would cost approximately $2,932 per airplane. 
Based on these figures, the cost impact of the terminating action 
proposed by this AD on U.S. operators is estimated to be $3,292 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 proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    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 2000-NM-303-AD.

    Applicability: Model 777-200 series airplanes, line numbers (L/
N) 1 through 9 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 per 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 prevent fracture of the inboard support structure of the 
flaperon, which could result in an in-flight loss of the inboard 
flaperon, structural damage, and consequent reduced controllability 
of the airplane, accomplish the following:

Repetitive Inspections

    (a) Before the accumulation of 4,000 total flight cycles, or 
within 90 days after the effective date of this AD, whichever occurs 
later: Do a detailed visual and an ultrasonic inspection of the 
lower flange of the flaperon inboard support to find cracks per Part 
1 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 777-57A0036, dated June 24, 1999.
    (1) If no cracking is found: Repeat the applicable inspections 
thereafter at intervals not to exceed 300 flight cycles until 
accomplishment of the terminating action specified in paragraph (b) 
of this AD.
    (2) If any cracking is found, before further flight, do the 
terminating action required by paragraph (b) of this AD, except, 
where the service bulletin specifies to contact Boeing for 
instructions, before further flight, 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 by the Manager, 
Seattle ACO, as required by this paragraph, the approval letter must 
specifically reference this AD.

Terminating Action

    (b) On or before the accumulation of 8,000 total flight cycles, 
or within 1,200 flight cycles after the effective date of this AD, 
whichever occurs later: Do the terminating action (a high frequency 
eddy current inspection to find cracks of the aft holes that attach 
the failsafe strap to the lower flange, oversizing of the holes if 
cracks are found, and installation of a failsafe strap), per Part 2 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
777-57A0036, dated June 24, 1999. Accomplishment of this paragraph 
terminates the repetitive inspections required by paragraph (a) of 
this AD.

Alternative Methods of Compliance

    (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, Seattle ACO, FAA. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may

[[Page 3523]]

add comments and then send it to the Manager, Seattle ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permit

    (d) Special flight permits may be issued per 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 January 9, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-1235 Filed 1-12-01; 8:45 am]
BILLING CODE 4910-13-P


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