[Federal Register Volume 68, Number 131 (Wednesday, July 9, 2003)]
[Proposed Rules]
[Pages 40827-40829]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-17318]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-207-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, 
-200B, -200C, -200F, -300, 747SR and 747SP Series Airplanes Equipped 
With Pratt & Whitney JT9D Series Engines

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 transport category 
airplanes listed above. This proposal would require drilling witness 
holes through the cowl skin at the cowl latch locations in the left-
hand side of the cowl panel assembly of each engine. This action is 
necessary to prevent improper connection of the latch, which could 
result in separation of a cowl panel from the airplane. Such separation 
could cause damage to the airplane, consequent rapid depressurization, 
and hazards to persons or property on the ground. This action is 
intended to address the identified unsafe condition.

DATES: Comments must be received by August 25, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-207-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. 2002-NM-207-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 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: Dan Kinney, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone 
(425) 917-6499; 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

[[Page 40828]]

in this action may be changed in light of the comments received.
    Submit comments using the following format:
    [sbull] 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.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] 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 2002-NM-207-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. 2002-NM-207-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received a report of in-flight separation of the cowl 
panels on the left- and right-hand sides of a Model 747 series 
airplane. Investigation revealed that the probable cause of the 
separation was improper latching of the cowl latch assemblies. The 
original cowl latch design allowed the latch to appear connected and 
latched, when it may not have been attached to the mating U-bolt. An 
improved design was developed for the latch to prevent incorrect 
latching, but in-service experience has shown that improper latching is 
still possible, even with the new latch. The addition of witness holes 
will allow the mechanic to visually inspect before a flight to 
determine that the cowl latch is properly connected. Improper 
connection of the latch could result in separation of a cowl panel from 
the airplane. Such separation could cause damage to the airplane, 
consequent rapid depressurization, and hazards to persons or property 
on the ground.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Service Bulletin 747-71-
2301, dated May 30, 2002, which describes procedures for drilling 0.50-
inch-diameter witness holes through the cowl skin at each of the six 
cowl latch locations located on the left-hand side of the cowl panel 
assembly of each engine. 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 specified in 
the service bulletin described previously, except as discussed below.

Explanation of Compliance Time

    We have determined that a compliance time of 36 months for 
initiating the proposed actions is warranted, in that it represents an 
appropriate interval of time allowable for affected airplanes to 
continue to operate without compromising safety.

Changes to 14 CFR Part 39/Effect on the Proposed AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance. Because we have now included this material in part 39, we 
no longer need to include it in each individual AD; however, this AD 
identifies the office authorized to approve alternative methods of 
compliance.

Explanation of Cost Increase

    We have reviewed the figures we have used over the past several 
years to calculate AD costs to operators. To account for various 
inflationary costs in the airline industry, we find it necessary to 
increase the labor rate used in these calculations from $60 per work 
hour to $65 per work hour. The cost impact information, below, has been 
revised to reflect this increase in the specified hourly labor rate.

Cost Impact

    There are approximately 345 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 108 airplanes of U.S. registry 
would be affected by this proposed AD, that it would take approximately 
8 work hours per airplane (2 work hours per engine) to accomplish the 
proposed actions, and that the average labor rate is $65 per work hour. 
Based on these figures, the cost impact of the proposed AD on U.S. 
operators is estimated to be $56,160, or $520 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.

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

[[Page 40829]]

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 2002-NM-207-AD.

    Applicability: Model 747-100, -100B, -100B SUD, -200B, -200C, -
200F, -300, 747SR, and 747SP series airplanes; equipped with Pratt & 
Whitney JT9D series engines; line numbers 1 through 669 inclusive; 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent improper connection of the cowl latch located in the 
left-hand side of the cowl panel assembly of each engine, which 
could result in separation of a cowl panel from the airplane, 
accomplish the following:

Drill Holes

    (a) Within 36 months after the effective date of this AD: Drill 
witness holes through the cowl skin at each of the six cowl latch 
locations located on the left-hand side of the cowl panel assembly 
of each engine, per paragraphs 3.B.1. through 3.B.4. of the 
Accomplishment Instructions of Boeing Service Bulletin 747-71-2301, 
dated May 30, 2002.

Alternative Methods of Compliance

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

    Issued in Renton, Washington, on July 1, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-17318 Filed 7-8-03; 8:45 am]
BILLING CODE 4910-13-P