[Federal Register Volume 69, Number 26 (Monday, February 9, 2004)]
[Proposed Rules]
[Pages 5939-5940]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-2680]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-182-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200 and -300 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 757-200 and -
300 series airplanes. This proposal would require inspection of the 
guide arm assembly on passenger door number 1 for a part mark to 
determine whether the guide arm assembly contains an adjuster rod which 
was incorrectly manufactured and replacement of any such adjuster rod. 
This action is necessary to prevent failure of the adjuster rod in the 
passenger door guide arm assembly, which could prevent the door from 
opening or closing during normal or emergency operations, resulting in 
inability to evacuate the crew and passengers in an emergency. This 
action is intended to address the identified unsafe condition.

DATES: Comments must be received by March 25, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-182-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#eed7c38f8083c3809e9c838d8183838b809aae888f8fc0898198"><span class="__cf_email__" data-cfemail="6a53470b040747041a1807090507070f041e2a0c0b0b440d051c">[email protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-182-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 the proposed rule 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.

FOR FURTHER INFORMATION CONTACT: David Crotty, Aerospace Engineer, 
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 917-6422; fax (425) 917-6590.

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<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 proposed 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 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 2001-NM-182-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. 2001-NM-182-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports that certain adjuster rods in 
passenger door guide arm assemblies of the number 1 left passenger 
doors on certain Boeing Model 757-200 and 757-300 series airplanes were 
improperly manufactured, resulting in adjuster rods which are not as 
strong as correctly manufactured adjuster rods. This condition, if not 
corrected, could result in failure of the adjuster rod in the passenger 
door guide arm assembly, which could prevent the door from opening or 
closing during normal or emergency operations, resulting in inability 
to evacuate the crew and passengers in an emergency.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Special Attention Service 
Bulletin 757-52-0077, dated February 15, 2001, (for Boeing Model 757-
200 series airplanes) and Boeing Special Attention Service Bulletin 
757-52-0078, dated February 15, 2001 (for Boeing Model 757-300 series 
airplanes). The service bulletins describe procedures for inspecting 
the guide arm assembly of the passenger door for a part mark and 
replacing the improperly manufactured adjuster rods in the guide arm 
assembly with new adjustor rods. The service bulletins also describe 
procedures for testing the hardness of an adjuster rod when there is no 
part mark on the guide arm assembly. Accomplishment of the actions 
specified in the service bulletins 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 these same type designs, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletins described previously.

Cost Impact

    There are approximately 9 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 9 airplanes of U.S. registry 
would be affected by this proposed AD, that it would take approximately 
1 work hour

[[Page 5940]]

per airplane to accomplish the proposed inspection, and that the 
average labor rate is $65 per work hour. Based on these figures, the 
cost impact of the proposed inspection on U.S. operators is estimated 
to be $585, or $65 per airplane.
    The FAA estimates that it would take approximately 2 work hours per 
airplane to accomplish the proposed replacement. Required parts would 
cost approximately $478 per airplane. Based on that figure, the cost 
impact of the proposed replacement on U.S. operators is estimated to be 
a maximum of $5,472, or $608 per airplane.
    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.
    The manufacturer would cover the cost of replacement parts and of 
labor associated with this proposed AD, subject to warranty conditions. 
As a result, the costs attributable to the proposed AD may be less than 
stated above.

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 2001-NM-182-AD.

    Applicability: Model 757-200 series airplanes, as listed in 
Boeing Special Attention Service Bulletin 757-52-0077, dated 
February 15, 2001, and Model 757-300 series airplanes, as listed in 
Boeing Special Attention Service Bulletin 757-52-0078, dated 
February 15, 2001; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the adjuster rod in the passenger door 
guide arm assembly, which could prevent the door from opening or 
closing during normal or emergency operations, resulting in 
inability to evacuate the crew and passengers in an emergency, 
accomplish the following:

Service Bulletin References

    (a) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of the following service bulletins, as 
applicable:
    (1) For Model 757-200 airplanes: Boeing Special Attention 
Service Bulletin 757-52-0077, dated February 15, 2001; and
    (2) For Model 757-300 airplanes: Boeing Special Attention 
Service Bulletin 757-52-0078, dated February 15, 2001.

Inspection of Part Mark

    (b) Within 18 months of the effective date of this AD: Inspect 
the part mark on the guide arm assembly of the number 1 left 
passenger door, in accordance with the applicable service bulletin.

Follow-on Actions

    (c) If the inspection of the part mark required by paragraph (b) 
of this AD reveals the name of a supplier, prior to further flight, 
accomplish the action specified in paragraph (c)(1) or (c)(2) of 
this AD, as applicable.
    (1) If the part mark of supplier CDSL is found on the guide arm 
assembly, then replace the adjuster rod of the guide arm assembly 
per Figure 2 of the applicable service bulletin.
    (2) If the part mark of a supplier other than CDSL is found on 
the guide arm assembly, then the adjuster rod is satisfactory, and 
no further action is required by this paragraph.
    (d) If no part mark is found during the inspection required by 
paragraph (b) of this AD, prior to further flight accomplish the 
action specified in either paragraph (d)(1) or (d)(2) of this AD.
    (1) Replace the adjuster rod of the guide arm assembly per 
Figure 2 of the applicable service bulletin.
    (2) Test the hardness of the adjuster rod of the guide arm 
assembly per Figure 3 of the applicable service bulletin.
    (i) If the hardness of the adjuster rod is less than 44 HRC 
(Rockwell C Hardness scale), then install a new adjuster rod per 
Figure 2 of the applicable service bulletin.
    (ii) If the hardness of the adjuster rod is greater than 44 HRC, 
then the adjuster rod is satisfactory, and no further action is 
required by this paragraph.

Parts Installation

    (e) As of the effective date of this AD, no person may install 
on any airplane an adjuster rod in any passenger door guide arm 
assembly which has either no part mark on the guide arm assembly or 
has the part mark of supplier CDSL.

Alternative Methods of Compliance

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

    Issued in Renton, Washington, on February 3, 2004.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-2680 Filed 2-6-04; 8:45 am]
BILLING CODE 4910-13-P


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