[Federal Register Volume 68, Number 222 (Tuesday, November 18, 2003)]
[Proposed Rules]
[Pages 64998-65000]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-28738]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-191-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727, 727-100C, 727-200F, 
and 727C 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 727, 727-
100C, 727-200F, and 727C series airplanes. This proposal would require 
repetitive open-hole high frequency eddy current inspections for cracks 
in the fuselage skin, strap (bearstrap), and doubler at the forward and 
aft hinge fittings for the main deck cargo door, and repair of any 
cracks found. This action is necessary to detect and correct such 
cracks, which could reach critical crack length and result in rapid 
decompression of the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Comments must be received by January 20, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-191-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. 2003-NM-191-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

[[Page 64999]]

Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437; 
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:
    [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 2003-NM-191-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. 2003-NM-191-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of multiple fatigue cracks in the 
fuselage skin, strap (bearstrap), and doubler at the forward and aft 
hinge fittings for the main cargo door on six airplanes. The cracks 
have been up to 0.15 inch long and have originated from the fastener 
holes common to the forward and aft main cargo door hinge fittings. The 
cracks have been found on airplanes with between 45,000 and 66,300 
flight hours, and between 34,000 and 50,000 flight cycles. The cracks 
were discovered during the accomplishment of the inspections specified 
in the Supplemental Structural Inspection Document. Such cracking, if 
not corrected, could reach critical crack length and result in rapid 
decompression of the airplane.

Explanation of Relevant Service Information

    We have reviewed and approved Boeing Alert Service Bulletin 727-
53A0226, dated September 11, 2003, which describes procedures for 
repetitive open-hole high frequency eddy current inspections for cracks 
in the fuselage skin, strap (bearstrap), and doubler at the forward and 
aft hinge fittings for the main deck cargo door. These inspections are 
recommended on airplanes before they have accumulated 30,000 total 
flight cycles, or within 1,500 flight cycles (or 3,000 flight cycles 
for freighters) after the effective date of the AD, whichever occurs 
later, and are repeated at intervals not to exceed 10,000 flight 
cycles. The fittings are located at body stations 486 and 610 and at 
stringer 3L. The service bulletin recommends that operators contact 
Boeing for repair instructions.

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 AD and Service Bulletin

    The service bulletin specifies compliance times relative to the 
date of the service bulletin; however, this proposed AD would require 
compliance with the thresholds after the effective date of the AD.
    Although the service bulletin specifies that operators may contact 
the manufacturer for disposition of certain repair conditions, this 
proposed AD would require operators to repair those conditions per a 
method approved by the Manager of the Seattle Aircraft Certification 
Office of 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.
    This proposed AD would also require that, within 12 months 
following a repair, operators implement an inspection program for the 
repair into the 727 maintenance program in accordance with a method and 
compliance times approved by the Manager, Seattle ACO; or per data 
meeting 14 CFR 25.571 (Amendment 25-54 or later) approved by a Boeing 
Company DER who has been authorized by the Manager, Seattle ACO, to 
make such findings. To ensure timely detection of cracking in those 
areas, we have determined that new inspection methods and compliance 
times are necessary for areas that have been repaired. The new 
inspection methods and compliance times should meet the requirements of 
14 CFR 25.571 (Amendment 25-54 or later).

Interim Action

    We consider this proposed AD interim action. If final action is 
later identified, we may consider further rulemaking then.

Cost Impact

    There are approximately 195 airplanes of the affected design in the 
worldwide fleet. We estimate that 133 airplanes of U.S. registry would 
be affected by this proposed AD. We provide the following cost 
estimates to comply with this proposed AD, per inspection cycle:

------------------------------------------------------------------------
                                           Hourly
             Group                Work     labor     Parts     Cost per
                                 hours      rate               airplane
------------------------------------------------------------------------
1.............................        7        $65       $0         $455
2.............................        8         65        0          520
3.............................        8         65        0          520
------------------------------------------------------------------------


[[Page 65000]]

    The cost impact figures discussed above are 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 2003-NM-191-AD.

    Applicability: Model 727, 727-100C, 727-200F, and 727C series 
airplanes, certificated in any category, as listed in Boeing Alert 
Service Bulletin 727-53A0226, dated September 11, 2003.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracks in the fuselage skin, strap 
(bearstrap), or doubler at the forward and aft hinge fittings for 
the main deck cargo door, which could reach critical crack length 
and result in rapid decompression of the airplane, accomplish the 
following:

Inspection

    (a) Perform an open-hole high frequency eddy current inspection 
for cracks in the fuselage skin, strap (bearstrap), and doubler at 
the forward and aft hinge fittings for the main deck cargo door. Do 
the inspection at the applicable initial compliance time listed in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
727-53A0226, dated September 11, 2003; except, where the service 
bulletin specifies a compliance time after the service bulletin 
date, this AD requires compliance within the specified compliance 
time after the effective date of this AD. Perform the inspection in 
accordance with the Accomplishment Instructions of the service 
bulletin.
    (1) If no crack is found: Repeat the inspection within the 
interval listed in paragraph 1.E., ``Compliance,'' of the service 
bulletin.
    (2) If any crack is found: Repair it before further flight in 
accordance with 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, the approval must specifically refer to this AD. Within 
12 months following a repair, implement an inspection program for 
the repair into the 727 maintenance program in accordance with a 
method and compliance times approved by the Manager, Seattle ACO; or 
per data meeting 14 CFR 25.571 (Amendment 25-54 or later) approved 
by a Boeing Company Designated Engineering Representative who has 
been authorized by the Manager, Seattle ACO, to make such findings.

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 November 12, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-28738 Filed 11-17-03; 8:45 am]
BILLING CODE 4910-13-P