[Federal Register Volume 69, Number 26 (Monday, February 9, 2004)]
[Rules and Regulations]
[Pages 5911-5913]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-2464]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-320-AD; Amendment 39-13449; AD 2004-03-05]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777-200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Model 777-200 series airplanes. This action 
requires a surface high frequency eddy current inspection of the web of 
the aft pressure bulkhead, repetitive inspections, and corrective 
action, if necessary. This action is necessary to detect and correct 
cracks or damage to the web of the aft pressure bulkhead, which could 
enlarge if undetected, leading to rapid decompression of the airplane 
and consequent possible loss of flight critical systems. This action is 
intended to address the identified unsafe condition.

DATES: Effective February 24, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 24, 2004.
    Comments for inclusion in the Rules Docket must be received on or 
before April 9, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-320-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#2c15014d424101454d5e4f4341414942586c4a4d4d024b435a"><span class="__cf_email__" data-cfemail="e2dbcf838c8fcf8b8390818d8f8f878c96a2848383cc858d94">[email protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-320-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 or 2000 or 
ASCII text.
    The service information referenced in this AD may be obtained from 
Boeing Commercial Airplanes, 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; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6443; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: The FAA received a report that parts of the 
radial lap splices at the station 2150 aft pressure bulkhead were 
covered up by a web repair made to the aft pressure bulkhead during 
production of two Boeing Model 777-200 series airplanes. The radial lap 
splices at the station 2150 aft pressure bulkhead require repetitive 
inspections as an Airworthiness Limitation, which is defined as 
Structural Significant Item (SSI) 53-80-I13 in Section 9 of Boeing 
Document D622W001, 777 Maintenance Planning Data. However, the web 
repairs made to the two Model 777-200 series airplanes could interfere 
with the detection of cracks or damage to the web during the required 
repetitive inspections. Undetected cracks or damage to the web, if not 
found and repaired, could result in the cracks enlarging, leading to 
rapid decompression of the airplane and consequent possible loss of 
flight critical systems.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
777-53A0039, dated November 14, 2002, which describes procedures for a 
surface high frequency eddy current (HFEC) inspection of the web of the 
aft pressure bulkhead, repetitive inspections, and corrective action, 
if necessary. The corrective action involves repairing any crack or 
damage found during any surface HFEC inspection. The surface HFEC 
inspections required by this AD would replace repetitive inspections of 
the radial lap splices in the local area of the web repair, required as 
an Airworthiness Limitation, which is defined as SSI 53-80-I13 in 
Section 9 of Boeing Document D622W001, 777 Maintenance Planning Data. 
Accomplishment of the actions specified in the service bulletin is 
intended to adequately address the identified unsafe condition.

Explanation of Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design that may be 
registered in the United States at some time in the future, this AD is 
being issued to detect and correct cracks or damage to the web of the 
aft pressure bulkhead, which could enlarge if undetected, leading to 
rapid decompression of the airplane and consequent possible loss of 
flight critical systems. This AD requires a surface HFEC inspection of 
the web of the aft pressure bulkhead, repetitive inspections, and 
corrective action, if necessary. The actions are required to be 
accomplished in accordance with the service bulletin described 
previously, except as discussed below.

Difference Between Proposed Rule and Service Bulletin

    Operators should note that, although the service bulletin specifies 
that operators may contact the manufacturer for repair data if cracks 
or damage is found, this proposed AD would require operators to repair 
any crack or damage 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.

[[Page 5912]]

Cost Impact

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes included in the applicability of this rule 
currently are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
the FAA considers that this rule is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject airplanes 
are imported and placed on the U.S. Register in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately between 2 and 4 
work hours (depending on airplane configuration) to accomplish the 
required actions, at an average labor rate of $65 per work hour. Based 
on these figures, the cost impact of this AD would be between $130 and 
$260 per airplane (depending on airplane configuration). Manufacturer 
warranty remedies may be available for labor costs associated with this 
AD. As a result, the costs attributable to the AD may be less than 
stated above.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
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 under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Submit comments using the following format:
    <bullet<ls-thn-eq> 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<ls-thn-eq> For each issue, state what specific change to 
the AD is being requested.
    <bullet<ls-thn-eq> 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 rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-320-AD.'' The postcard will be date stamped 
and returned to the commenter.

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

0
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

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-03-05 Boeing: Amendment 39-13449. Docket 2002-NM-320-AD.

    Applicability: Model 777-200 series airplanes, variable numbers 
WA207 and WB325; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracks or damage to the web of the aft 
pressure bulkhead, which could enlarge if undetected, leading to 
rapid decompression of the airplane and consequent possible loss of 
flight critical systems, accomplish the following:

Initial and Repetitive Inspections

    (a) Prior to the accumulation of 30,000 total flight cycles, do 
a surface high frequency eddy current (HFEC) inspection to find 
cracks or damage to the web of the station 2150 aft pressure 
bulkhead from the forward side, per the Accomplishment Instructions 
of Boeing Alert Service Bulletin 777-53A0039, dated November 14, 
2002. Repeat the surface HFEC inspection thereafter at intervals not 
to exceed 16,000 flight cycles.

Corrective Action

    (b) If any crack or damage is found during any surface HFEC 
inspection required by paragraph (a) of this AD, and the service 
bulletin specifies to ask Boeing for repair data: 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 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 Manager's approval letter must 
specifically refer to this AD.

Alternative Methods of Compliance

    (c) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, 
FAA, is authorized to approve alternative methods of compliance 
(AMOCs) for this AD.

Incorporation by Reference

    (d) Unless otherwise specified by this AD, the actions shall be 
done in accordance with Boeing Alert Service Bulletin 777-53A0039, 
dated November 14, 2002. 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 Airplanes, 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

[[Page 5913]]

Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (e) This amendment becomes effective on February 24, 2004.

    Issued in Renton, Washington, on January 29, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-2464 Filed 2-6-04; 8:45 am]
BILLING CODE 4910-13-P


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