[Federal Register Volume 66, Number 247 (Wednesday, December 26, 2001)]
[Proposed Rules]
[Pages 66360-66362]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-31558]



[[Page 66360]]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-382-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Boeing Model 767-200 
series airplanes. This proposal would require repetitive inspections of 
the side panels of the nose wheel well for broken rivets and 
replacement of any broken rivets with bolts. This proposal would also 
require follow-on inspections of adjacent areas for cracks or broken 
rivets, whenever two or more adjacent broken rivets are found; repair 
of any cracks; and replacement of any broken rivets with bolts. 
Finally, this proposal provides for the optional replacement of all 
rivets in the affected area with bolts, which would terminate the 
repetitive inspections. This action is necessary to detect and correct 
broken rivets in the nose wheel well side panels and top panel, which 
could impair the function of the nose landing gear and cause fatigue 
cracks in the side panel and top panel webs of the nose wheel well, 
which could result in rapid cabin depressurization during flight. This 
action is intended to address the identified unsafe condition.

DATES: Comments must be received by February 11, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket Number 2000-NM-382-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: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-382-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: John Craycraft, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2782; 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:
     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.
     For each issue, state what specific change to the proposed 
AD is being requested.
     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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-382-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 Number 2000-NM-382-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received a report indicating that 155 broken rivets 
were found in the side and top panels of the nose wheel well on a 
Boeing Model 767-200 airplane. Analysis indicates that pressurization 
loads on the side panel and top panel webs results in high prying loads 
on these rivets. Broken rivets in the side and top panels of the nose 
wheel well, if not corrected, could impair the function of the nose 
landing gear and cause fatigue cracks in the side and top panel webs of 
the nose wheel well, which could result in rapid cabin depressurization 
during flight.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Service Bulletin 767-
53A0090, Revision 1, dated September 14, 2000, which describes 
procedures for repetitive inspections of the nose wheel well side 
panels for broken rivets and replacement of any broken rivets with 
bolts. The service bulletin also describes procedures for follow-up 
inspections of adjacent areas for broken rivets and cracks, whenever 
two or more adjacent broken rivets are found; repair of any cracks; and 
replacement of any broken rivets with bolts. Finally, the service 
bulletin describes procedures for the optional replacement of all 
rivets in the affected area with bolts, which eliminates the need for 
repetitive inspections.

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 rule would require accomplishment of the actions specified in 
the service bulletin described previously, except as described below.

Differences Between Service Bulletin and Proposed Rule

    Operators should note that the service bulletin specifies that if 
broken rivets are found during a secondary inspection, they must be 
repaired, and that repair data should be requested from the Boeing 
Company. However, this proposed rule would require the repair to be 
accomplished per a method

[[Page 66361]]

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 Manager, Seattle Aircraft 
Certification Office, to make such findings.

Cost Impact

    There are approximately 62 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 46 airplanes of U.S. registry 
would be affected by this proposed AD, that it would take approximately 
2 work hours per airplane to accomplish the proposed inspection, and 
that the average labor rate is $60 per work hour. Based on these 
figures, the cost impact of the proposed AD on U.S. operators is 
estimated to be $5,520, or $120 per airplane, per inspection cycle.
    The cost impact figure discussed above is 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-382-AD.

    Applicability: Model 767 series airplanes, line numbers 1 
through 62; 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 detect and correct broken rivets in the nose wheel well side 
panels and top panel, which could impair the function of the nose 
landing gear and cause fatigue cracks in the nose wheel well side 
panel and top panel webs, which could result in rapid cabin 
depressurization during flight, accomplish the following:

Initial and Repetitive Inspections

    (a) Within 18 months or 3,000 flight cycles after the effective 
date of this AD, whichever occurs first: Perform a detailed visual 
inspection of the nose wheel well side panels for broken rivets, in 
accordance with Boeing Service Bulletin 767-53A0090, Revision 1, 
dated September 14, 2000.

    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.''


    Note 3: Inspections, replacement, and repairs performed prior to 
the effective date of this AD in accordance with Boeing Service 
Bulletin 767-53A0090, dated August 3, 2000, are considered 
acceptable for compliance with the applicable actions specified in 
this amendment.

    (1) If no broken rivets are detected: No further action is 
required as part of the initial inspection. Repeat the inspection at 
intervals not to exceed 18 months or 3,000 flight cycles, whichever 
occurs first.
    (2) If broken rivets are detected, but they do not include two 
or more adjacent rivets: Prior to further flight, replace the broken 
rivets with bolts in accordance with the service bulletin. Repeat 
the inspection at intervals not to exceed 18 months or 3,000 flight 
cycles, whichever occurs first.
    (3) If two or more adjacent broken rivets are detected: Prior to 
further flight, perform a secondary inspection as specified in 
paragraph (c) of this AD.

Optional Terminating Action

    (b) Replacement of all the rivets with bolts in accordance with 
Figure 5 of Boeing Service Bulletin 767-53A0090, Revision 1, dated 
September 14, 2000, terminates the repetitive inspection required by 
paragraph (a) of this AD.

Secondary Inspections

    (c) If two or more adjacent broken rivets are found during any 
inspection required by paragraph (a) of this AD: Prior to further 
flight, perform a detailed visual inspection of the side panels and 
the top panel of the nose wheel well for cracks or broken rivets, in 
accordance with Boeing Service Bulletin 767-53A0090, Revision 1, 
dated September 14, 2000.
    (1) If no cracks or additional broken rivets are found: Prior to 
further flight replace all of the rivets with bolts in accordance 
with Figure 5 of the service bulletin. This terminates the 
repetitive inspections required by paragraph (a) of this AD.
    (2) If any cracks or additional broken rivets are found: Prior 
to further flight, repair the cracks and replace all of the rivets, 
per a method approved by the Manager, Seattle Aircraft Certification 
Office, 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 reference this AD. This terminates 
the repetitive inspections required by paragraph (a) 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 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.


[[Page 66362]]


    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

    (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 December 17, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 01-31558 Filed 12-21-01; 8:45 am]
BILLING CODE 4910-13-U