[Federal Register Volume 66, Number 229 (Wednesday, November 28, 2001)]
[Proposed Rules]
[Pages 59384-59386]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-29598]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-203-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 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 all Boeing Model 727 series 
airplanes. This proposal would require repetitive inspections for 
cracking of the upper chord of the rear spar of the wing, and 
corrective action, if necessary. This action is necessary to find and 
fix such cracking, which could result in fuel

[[Page 59385]]

leaking through the cracks, reduced structural integrity of the wing, 
and separation of the wing from the airplane. This action is intended 
to address the identified unsafe condition.

DATES: Comments must be received by January 14, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-203-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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. 2001-NM-203-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: Walter Sippel, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2774; 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 2001-NM-203-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-203-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports that fatigue cracking has been found 
in the upper chord of the rear spar of the wing at approximately wing 
station (WS) 293 on several Boeing Model 727 series airplanes. In most 
cases, the cracking was discovered during inspections to determine the 
source of fuel leaks on the left wing of the airplane. All of the 
cracks were fully through the vertical flange of the chord, and several 
extended into the horizontal flange to the first row of fasteners that 
attach the skin of the wing to the chord. During routine visual 
inspections, this cracking would not be seen until it extends from 
under the flanges of the stiffener installed at WS 293. Cracking of the 
upper chord of the rear spar, if not corrected, could result in fuel 
leaking through the cracks, reduced structural integrity of the wing, 
and separation of the wing from the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Service Bulletin 727-57-
0184, dated August 16, 2001, which describes procedures for repetitive 
detailed visual and high frequency eddy current inspections for 
cracking of the upper chord of the rear spar at approximately WS 293. 
The detailed visual inspection also includes an inspection of the 
surface finish for damage or deterioration (discoloration, blistering, 
raised or rough areas), removal of the finish, if necessary, and 
blending of the area until smooth, if necessary. If any cracking is 
found, the service bulletin specifies to contact Boeing for repair 
instructions. 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.

Differences Between Proposed Rule and Service Bulletin

    Operators should note that, although the service bulletin specifies 
that the manufacturer may be contacted for disposition of certain 
repair conditions, this proposal would require the repair of those 
conditions to be accomplished according to a method approved by the 
FAA, or according to data meeting the type certification basis of the 
airplane approved by a Boeing Company Designated Engineering 
Representative (DER) who has been authorized by the FAA to make such 
findings.
    Operators also should note that, if any damage or deterioration, 
but no cracking, is found during the proposed inspection, the proposed 
AD would require removal of the finish, blending of the area until 
smooth, and reapplication of the finish. However, if the necessary 
blend-out is outside the limits specified in the Boeing 727 SRM, the 
proposed AD would require repair according to a method approved by the 
FAA or according to data meeting the type certification basis of the 
airplane approved by a Boeing Company DER who has been authorized by 
the FAA to make such findings.
    Operators also should note that, although the effectivity summary 
in paragraph 1.A.1. of the referenced service bulletin identifies only 
Model 727-100 and -200 series airplanes as being subject to the actions 
specified in the service bulletin, we have determined that the proposed 
actions apply to all Model 727 series airplanes, including Model 727, 
727-100C, 727-200F, and 727C series airplanes.

[[Page 59386]]

Cost Impact

    There are approximately 1,375 airplanes of the affected design in 
the worldwide fleet. The FAA estimates that 912 airplanes of U.S. 
registry would be affected by this proposed AD, that it would take 
approximately 12 work hours per airplane to accomplish the proposed 
inspections, 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 $656,640, or $720 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 2001-NM-203-AD.

    Applicability: All Model 727 series airplanes, 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 (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 find and fix cracking of the upper chord of the rear spar of 
the wing, which could result in fuel leaking through the cracks, 
reduced structural integrity of the wing, and separation of the wing 
from the airplane, accomplish the following:

Repetitive Inspections

    (a) Prior to the accumulation of 20,000 total flight cycles, or 
within 500 flight cycles after the effective date of this AD, 
whichever is later, do detailed visual and high frequency eddy 
current inspections for cracking of the upper chord of the rear spar 
of the wing, according to Boeing Service Bulletin 727-57-0184, dated 
August 16, 2001. The detailed visual inspection must include an 
inspection of the surface finish for damage or deterioration 
(discoloration, blistering, raised or rough areas), as described in 
the service bulletin. Repeat all inspections every 4,500 flight 
cycles.

    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.''

Repairs

    (b) If any cracking, damage, or deterioration is found during 
any inspection required by paragraph (a) of this AD: Before further 
flight, do paragraph (b)(1) or (b)(2) of this AD, as applicable.
    (1) If any damage or deterioration but no cracking is found, 
remove the finish, blend the area smooth, and reapply the finish 
according to Boeing Service Bulletin 727-57-0184, dated August 16, 
2001.
    (i) If the blend-out is within the limits specified in Section 
57-10-1 of the Boeing 727 Structural Repair Manual (SRM), no further 
action is required by this paragraph.
    (ii) If the blend-out is outside the limits specified in Section 
57-10-1 of the Boeing 727 SRM, before further flight, repair 
according to a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA; or according to 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 Manager's approval letter must 
specifically reference this AD.
    (2) If any cracking is found, repair according to a method 
approved by the Manager, Seattle ACO, or according to data meeting 
the type certification basis of the airplane approved by a Boeing 
Company 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 Manager's 
approval letter must specifically reference 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. 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.

    Note 3: 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

    (d) 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 November 21, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-29598 Filed 11-27-01; 8:45 am]
BILLING CODE 4910-13-U